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AERADE Reports Archive

ARC/CP listing

    1. 


    ARC/CP-528

    CANCELLED AS CP

    Available from:


    2. 


    ARC/CP-1104

    PUBLICATION DISCONTINUED

    Available from:


    3. The indication of boundary-layer transition on aerofoils in the N.P.L. 20 in. x 8 in. high speed wind tunnel

    H.H. Pearcey
    ARC/CP-10
    14th December 1948

    The "liquid film" evaporation method developed by Gray for indicating the position of boundary-layer transition on models in low speed wind tunnels has proved satisfactory in the N.P.L. 20 in. x 8 in. high speed tunnel. Observation of transition over the complete span of the model can be simultaneous with that of surface pressures, profile drag and flow pattern. Direct shadow photographs taken in this tunnel also give an approximate indication of the transition point in certain cases, due to the change in density profile accompanying the change from laminar to turbulent flow. Thus, except when transition occurs near the leading edge,a laminar layer is indicated by a bright line parallel to, but separated from, the dark shadow of the aerofoil and converging on to this shadow to moot it just downstream of the transition point.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0010.pdf


    4. Porous Properties of Various Materials liable to be used for Making Parachutes

    W. D. Brown, M.Sc., A.M.I.Mech.E. and J. F. Holford
    ARC/CP-24
    March, 1949

    An investigation has been made into the porous properties of paper perforated with round holes, and ribbon meshes with square interspaces. It has been established that the relationship between porosity and the porous area is almost linear for all materials.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0024.pdf


    5. A comparison of three thick, symmetrical, multi-slot suction aerofoils

    N. Gregory and A. R. Curtis
    ARC/CP-20
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0020.pdf


    6. A recording system for flight test data

    P. A. Hufton, F. G. R. Cook, and P. S. Saunders
    ARC/CP-44
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0044.pdf


    7. Air bags as flexible supports in ground resonance testing of aircraft

    R.L. Moffat and d.R. Gaukroger
    ARC/CP-32
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0032.pdf


    8. An approximate method for the estimation of the design point efficiency of axial flow turbines

    D.G. Ainley
    ARC/CP-30
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0030.pdf


    9. An electronic analyser for linear differential equations

    J.J. Gait and D.W. Allen
    ARC/CP-23
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0023.pdf


    10. Camber derivatives and two-dimensional tunnel interference at maximum lift

    R. C. Pankhurst and H. H. Pearcey
    ARC/CP-28
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0028.pdf


    11. Determination of the static stability of seaplanes

    K.M. Tomaszewski
    ARC/CP-14
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0014.pdf


    12. Full scale measurements of impact loads on a large flying boat part 1 description of apparatus and instrument installation

    J.W. McIver
    ARC/CP-182
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0182.pdf


    13. Hydrodynamic design of seaplane floats

    K. M. Tomaszewski
    ARC/CP-15
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0015.pdf


    14. Influence of variable specific heats on the high-speed flow of air

    J. Kestin
    ARC/CP-33
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0033.pdf


    15. Low-speed tunnel investigation of the effect of the body on Cmo and aerodynamic centre of unswept wing-body combinations

    A. Anscombe and D. J. Raney
    ARC/CP-16
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0016.pdf


    16. Maximum impact pressures on seaplane hull bottoms

    A. G. Smith, I. W. McCaig, W. M. Inverarity
    ARC/CP-4
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0004.pdf


    17. Note on sintered metal with a view to its use as a porous surface in distributed suction experiments

    J. H. Preston and A. G. Rawcliffe
    ARC/CP-9
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0009.pdf


    18. Note on the interference on a part-wing mounted symmetrically on one wall of a wind-tunnel of octagonal section

    H. C. Garner
    ARC/CP-5
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0005.pdf


    19. Preliminary measurements of the aerodynamic damping in pitch of a 12 ft diameter helicopter rotor

    C.M. Britland and R.A. Fail
    ARC/CP-22
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0022.pdf


    20. Report on measurements of the pressure distribution over a wing of triangular plan form at a Mach number of 2.44

    G.H. Lean, and K.G. Whitaker
    ARC/CP-7
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0007.pdf


    21. Revised and extended performance characteristics of ram jets

    D.F. Collins and Frances M. Gordon
    ARC/CP-11
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0011.pdf


    22. Some improvements in the design of thick suction aerofoils

    J. Williams
    ARC/CP-31
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0031.pdf


    23. Some investigations into the design of wind tunnels with gas turbine jet engine drives

    H.J. Higgs
    ARC/CP-107
    May 1950

    The basic design of wind tunnels suitable for jet engine drives has been investigated by matching the predicted mass flows and total pressure losses of typical tunnel configurations with the estimated mass flow and total pressure rise characteristics of possible pumping systems. There are three possibilities of jet engine pumping (i) induction pumping (ii) suction pumping and (iii) parallel suction and induction pumping, of which induction pumping is shown to be the most favourable.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0107.pdf


    24. Some notes on the flapping motion of rotor blades

    J.B.B. Owen
    ARC/CP-1
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0001.pdf


    25. Stability tests on a large scale model of the shetland hull bottom

    H. G. White, A. G. Smith
    ARC/CP-27
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0027.pdf


    26. Tank tests on the effect of slipstream on the water performance of a large four engined flying boat (Shetland 1)

    S. Raymond
    ARC/CP-6
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0006.pdf


    27. Tests in the N.P.L. electric tank on a 4:1 axi-symmetrical diffuser having a discontinuity in the wall velocity

    F. Cheers and W. G. Raymer
    ARC/CP-2
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0002.pdf


    28. The annealing of formed perspex structures

    E.W. Russell
    ARC/CP-19
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0019.pdf


    29. The application of jet propulsion to helicopters

    Wm. Stewart and M.F. Burle
    ARC/CP-8
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0008.pdf


    30. The effect of propeller thrust on downwash and velocity at tailplane - a collection of data from low speed wind tunnel tests

    A. Spence
    ARC/CP-21
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0021.pdf


    31. The effect of variation of air density and temperature on the airflow characteristics of porous fabrics

    J. Picken
    ARC/CP-25
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0025.pdf


    32. The electronic simulator for the solution of flutter and vibration problems

    F. Smith
    ARC/CP-26
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0026.pdf


    33. The heat treatment of flat perspex sheets

    E. W. Russell
    ARC/CP-18
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0018.pdf


    34. The low speed performance of related aerofoils in cascade

    A. D. S. Carter
    ARC/CP-29
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0029.pdf


    35. The viscid flow of air in a narrow slot

    G.L. Shires
    ARC/CP-13
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0013.pdf


    36. Transitional friction effects in powered controls with particular reference to hydraulic jacks

    F. Holoubek
    ARC/CP-12
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0012.pdf


    37. Water stability tests on Saro 37 fitted with shetland hull bottom, wing-tip floats, and tail

    I. W. McCaig
    ARC/CP-3
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0003.pdf


    38. Wind tunnel tests on a one-twelfth scale model of a twin-engined military transport. (airspeed C 13/45 ayrshire)

    R. Warden
    ARC/CP-17
    1950

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0017.pdf


    39. A note on the use of time series in the analysis of flight test records

    W. P. Jones
    ARC/CP-46
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0046.pdf


    40. A theoretical and experimental investigation of the flow in a duct of varying cross-section, with particular application to the design of ducts for free flight ground-launched model tests

    C.H.E. Warren, R.E. Dudley and P.J. Herbert
    ARC/CP-60
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0060.pdf


    41. A three-channel piezo-electric pressure recorder

    P.J. Fletcher
    ARC/CP-35
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0035.pdf


    42. Calculation of the damping for rolling oscillations of a swept wing

    Doris E. Lehrian
    ARC/CP-51
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0051.pdf


    43. Cockpit lighting a general survey of the principles and techniques with particular reference to the development of the dual system

    E.S. Calvert
    ARC/CP-36
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0036.pdf


    44. Comparison between experimental measurements and a suggested formula for the variation of turbulent skin-friction in compressible flow

    R. J. Monaghan
    ARC/CP-45
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0045.pdf


    45. Data on flight loads obtained with Miller recording equipment, with particular reference to test flights in lancaster PD. 119

    Anne Burns
    ARC/CP-48
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0048.pdf


    46. Dynamic stability of the helicopter the equations of motion

    A. H. Yates
    ARC/CP-47
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0047.pdf


    47. Focussing Schlieren systems

    R.W. Fish and K. Parnham
    ARC/CP-54
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0054.pdf


    48. Free flight measurements at supersonic speeds of the drag of a particular delta wing having a simple pressure distribution

    P. J. Herbert
    ARC/CP-57
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0057.pdf


    49. Full scale measurements of impact loads on a large flying boat (sunderland Mk.5) part 2 results for impacts on main step

    J. A. Hamilton
    ARC/CP-205
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0205.pdf


    50. Further wind tunnel tests on the effects of ice accretion on control characteristics

    A. Spence
    ARC/CP-43
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0043.pdf


    51. List of current papers published for the Aeronautical Research Council (numbers 1-50)

    Aeronautical Research Council
    ARC/CP-50
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0050.pdf


    52. Low-speed wind tunnel investigation of the change in aerodynamic centre position and in Cmo due to propeller turbine nacelles

    D.A. Kirby and F.W. Dee
    ARC/CP-39
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0039.pdf


    53. Notes on definitions of and nomenclature for air speeds

    Aeroplane and armament experimental Establishment
    ARC/CP-49
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0049.pdf


    54. Observations of the interaction between the shock waves and boundary layers at the trailing edges of aerofoils in supersonic flow

    D. W. Holder and R. J. North
    ARC/CP-53
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0053.pdf


    55. Observations of the supersonic flow round a 6 per cent double wedge

    D. W. Holder, A. Chinneck, and D. G. Hurley
    ARC/CP-63
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0063.pdf


    56. Pressure measurements in a supersonic tunnel on a two-dimensional aerofoil of R.A.E. 104 section

    D. W. Holder, A. Chinneck, and R. J. North
    ARC/CP-62
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0062.pdf


    57. Some curves for use in calculations of the performance of conical centrebody intakes at supersonic speeds and at full mass flow

    L.E. Fraenkel
    ARC/CP-108
    December 1951

    This note presents curves of a number of parameters which frequently Occur in calculations of the performance of conical centrebody intakes at supersonic speeds and full mass flow. These parameters follow directly from the theoretical supersonic flow past cones. Semi-cone angles of 15°, 20°, 22.5°, 25°, and 30° are considered, and the range of free stream Mach number is approximately 1.3 to 3.0.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0108.pdf


    58. Some effects of Reynolds number on a cambered wing at high subsonic Mach numbers

    H.E. Gamble
    ARC/CP-103
    May 1951

    An untapered, sweptback wing of aspect ratio 4, sweepback 25 degrees and section 12% thick (R.A.E. 104 with 1% camber, a = 0.6) was tested in the R.A.E. Hqh Speed Tunnel. The pressure distribution was measured at the mid-semispan section at various Mach numbers up to 0.88 at Reynolds numbers of 0.8, 1.8 and 3.5 x 10 to the power 6.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0103.pdf


    59. Swept-wing loading a critical comparison of four subsonic vortex sheet theories

    H. C. Garner, L. W. Bryant
    ARC/CP-102
    July 1951

    From a systematic series of calculations of swept-wing loading the writer has formed an opinion of the accuracy and most useful application of vortex lattice theory and the vortex sheet theories of Weissinger, Multhopp and Kuchemann. The results provide a general picture of the effect of sweep and compressibility on lift slope and aerodynamic centre.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0102.pdf


    60. Tests on A.W. Apollo (Brab 2B) in the N.P.L. compressed air tunnel

    C. Salter, C. J. W. Miles and P. S. Pusey
    ARC/CP-40
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0040.pdf


    61. Tests on the effect of incidence on some pressure heads at high subsonic speeds

    E. W. E. Rogers, and C. J. Berry
    ARC/CP-41
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0041.pdf


    62. The air flow under the towing carriages in the R.A.E. seaplane tank

    K.M. Tomaszewski, S. Raymond, G.F. Chalmers
    ARC/CP-38
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0038.pdf


    63. The design of Jettisonable cockpit hoods

    I. L. Keiller
    ARC/CP-105
    September 1951

    In the past much trouble has been experienced in the design of jettisonable cockpit hoods and even after a considerable amount of development many hoods are not really satisfactory. In order that a successful hood jettisoning mechanism can be produced it is essential that the various problems involved should be realised at the design stage. Consideration is given in this Note to the jettisoning problems involved in the design of all types of hoods and cockpit covers. Certain basic design criteria are proposed and the various methods of meeting them are discussed. Recommendations on good design practice are given where possible. With the knowledge that is at present available the design of a satisfactory orthodox hood should present no great problems, but the more advanced designs are likely to cause some difficulty.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0105.pdf


    64. The effect of induced velocity variation on helicopter rotor damping in pitch or roll

    G. J. Sissingh
    ARC/CP-101
    November 1951

    Tne present investigation is a continuation of a recent report by K. B. Amer on the aerodynamcc damping of a rotor with centrally arranged flapping hinges in a steady pitching or rolling motion. It considers the effect of variation in the induced velocity due to the changes in the distribution of the thrust around the rotor disc. The results are compared with the flight measurements given in Amer's report and the agreement 1s good. The rotor damping primarily depends on two quantities:- (a) the ratio of collective pitch to the thrust coefficient + solidity ratio (already found by Amer), and b) tip speed ratio x rotor angle of attack divided by collective pitch. With regard to the latter, the damping is increased if this expression is positive and decreased if it is negative. This means an increase in damping in autorotation and a loss in damping for helicopter flight, especially at higher tip speed ratios or in climbing flight.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0101.pdf


    65. The experimental approach to the problems of shaft whirling

    E. Downham
    ARC/CP-55
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0055.pdf


    66. The incompressible potential flow past two-dimensional aerofoils with arbitrary surface suction

    W. T. Lord
    ARC/CP-56
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0056.pdf


    67. The measurement of heat transfer and skin friction at supersonic speeds: preliminary results of measurements on a flat plate at a mach number of 2.5

    J.E. Johnson and R.J. Monaghan
    ARC/CP-59
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0059.pdf


    68. The measurement of the derivative zw for an oscillating aerofoil

    A.L. Buchan, K.D. Harris, and P.M. Somervail
    ARC/CP-52
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0052.pdf


    69. The pressures on the surface of a flat elliptic cone set symmetrically in a supersonic stream

    D. G. Hurley
    ARC/CP-109
    7th November 1951

    The first order solution of the problem of the supersonic flow past a flat elliptic cone set symmetrically to the wind indicates that the pressure over the surface is constant if the body lies within the Mach cone of the apex. This result is incorrect near the leading edges of the cone and an improved solution is derived here by the introduction of line sources near the leading edges. Numerical results are given for three bodies.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0109.pdf


    70. The supersonic pressure drag of a swept wing with a cranked maximum thickness line

    K. D. Thomson
    ARC/CP-61
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0061.pdf


    71. The theoretical lift and pitching moment of a highly-swept delta wing on a body of elliptic cross-section

    T. Nonweiler
    ARC/CP-58
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0058.pdf


    72. Torsional vibration investigations on the musketeer engine

    E. Downham, Winifred Davidson and M.O.W. Wolfe
    ARC/CP-34
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0034.pdf


    73. Wind tunnel tests on a Griffith meteor model (without suction)

    D.A. Clarke
    ARC/CP-37
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0037.pdf


    74. Wind tunnel tests on the effect of accretion of ice on control characteristics in two-dimensional flow

    A. S. Halliday, A. S. Batson, and D. K. Cox
    ARC/CP-42
    1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0042.pdf


    75. A brief survey of some methods and information concerning the aerodynamic derivatives of wings in unsteady motion at transonic and supersonic speeds

    W. E. A. Acum
    ARC/CP-85
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0085.pdf


    76. An assessment of the probable causes of variation of the speed correction coefficient of aircraft thermometers

    D. D. Clark
    ARC/CP-91
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0091.pdf


    77. An experimental investigation of the performance of a pilot plant for drying air by solid granular adsorbents

    P.J. Bateman
    ARC/CP-79
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0079.pdf


    78. Approximate two-dimensional aerofoil theory part 1 velocity distributions for symmetrical aerofoils

    S. Goldstein
    ARC/CP-68
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0068.pdf


    79. Approximate two-dimensional aerofoil theory part 2 velocity distributions for cambered aerofoils

    S. Goldstein
    ARC/CP-69
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0069.pdf


    80. Approximate two-dimensional aerofoil theory part 3 approximate designs of symmetrical aerofoils for specified pressure distributions

    S. Goldstein, and E. J. Richards
    ARC/CP-70
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0070.pdf


    81. Approximate two-dimensional aerofoil theory part 4 the design of centre lines

    S. Goldstein
    ARC/CP-71
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0071.pdf


    82. Approximate two-dimensional aerofoil theory part 5 the positions of maximum velocity and theoretical CL-ranges

    S. Goldstein
    ARC/CP-72
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0072.pdf


    83. Approximate two-dimensional aerofoil theory part 6 aerofoils with hinged flaps

    S. Goldstein, and J. H. Preston
    ARC/CP-73
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0073.pdf


    84. Calculated Pressure Distributions for the R.A.E. 100-104 Aerofoil Sections

    R. C. Pankhurst and H. B. Squire
    ARC/CP-80
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0080.pdf


    85. Comparison of helicopter rotor model tests of aerodynamic damping with theoretical estimates

    G.J. Sissingh
    ARC/CP-98
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0098.pdf


    86. Designing a slot for a given wall velocity

    A. Thom and Laura Klanfer
    ARC/CP-76
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0076.pdf


    87. Designing to avoid dangerous behaviour of an aircraft due to the effects on control hinge moments of ice on the leading edge of the fixed surface

    D. E. Morris
    ARC/CP-66
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0066.pdf


    88. Digital recording and analysing of flight test data a proposed system

    E.J. Petherick
    ARC/CP-75
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0075.pdf


    89. Draft corrections for water surface deflection under no.1 carriage of the R.A.E. seaplane tank

    T.B. Owen
    ARC/CP-67
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0067.pdf


    90. Experiments on distributed suction through a rough porous surface

    Cambridge University Aeronautical Laboratory
    ARC/CP-84
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0084.pdf


    91. Fatigue tests on typical two spar light alloy structures (meteor 4 tailplanes) under reversed loading

    K.D. Raithby
    ARC/CP-88
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0088.pdf


    92. Flight tests on the Youngman-Baynes high-lift experimental aircraft

    D. Lean
    ARC/CP-65
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0065.pdf


    93. Fluid dynamic notation in current use at N.G.T.E

    S. Gray
    ARC/CP-97
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0097.pdf


    94. Graphical solution of multhopp's equations for the lift-distribution of wings

    F. Vandrey
    ARC/CP-96
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0096.pdf


    95. Helicopter behaviour in the vortex ring conditions

    Wm. Stewart
    ARC/CP-99
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0099.pdf


    96. High speed wind tunnel tests on an aerofoil with and without two-dimensional spanwise bulges

    J. A. Beavan, E. W. E. Rogers, and R. Cartwright
    ARC/CP-78
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0078.pdf


    97. Improper integrals in theoretical aerodynamics

    K.W. Mangler
    ARC/CP-94
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0094.pdf


    98. List of current papers published for the Aeronautical Research Council (numbers 51-100)

    Aeronautical Research Council
    ARC/CP-100
    August, 1952

    This paper lists fifty titles which have been published in the CP Series of the Aeronautical Research Council.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0100.pdf


    99. N.P.L. Aerofoil catalogue and bibliography

    R. C. Pankhurst
    ARC/CP-81
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0081.pdf


    100. Notes and graphs for boundary layer calculations in compressible flow

    W. F. Cope
    ARC/CP-89
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0089.pdf


    101. Notes on the derivation of true air temperature from aircraft observations

    D. D. Clark
    ARC/CP-90
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0090.pdf


    102. Power requirements for distributed suction for increasing maximum lift

    R. C. Pankhurst, and N. Gregory
    ARC/CP-82
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0082.pdf


    103. Pressure and boundary layer measurements on a 59 degrees sweptback wing at low speed and comparison with high speed results on a 45 degrees swept wing part 1 part 2

    Aero Department, Royal Aircraft Establishment
    ARC/CP-86
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0086.pdf


    104. Structural aspects of suction wings

    E.H. Mansfield
    ARC/CP-87
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0087.pdf


    105. Tests in the compressed air tunnel on two aerofoil sections having a large scale effect on CLmax at a critical reynolds number

    C. Salter, H. M. Lee and R. C. Owen
    ARC/CP-92
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0092.pdf


    106. The diffusion of transverse loads in a reinforced circular cylinder with non-rigid frames

    S.R. Lewis
    ARC/CP-74
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0074.pdf


    107. The Effect of Endplates on Swept Wings

    D. Kuchemann and D. J. Kettle
    ARC/CP-104
    June, 1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0104.pdf


    108. The effects of atmospheric humidity and temperature on the engine power and take-off performance of a hastings 1

    G. Jackson
    ARC/CP-77
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0077.pdf


    109. The influence of the method of stringer attachment on the buckling and failure of skin panels with square top-hat stringers an abstract from the thesis of E.E. Labram, D.C.Ae

    K.H. Griffin
    ARC/CP-93
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0093.pdf


    110. The measurement of heat transfer and skin friction at supersonic speeds part 2 boundary layer measurements on a flat plate at M = 2.5 and zero heat transfer

    R. J. Monaghan and J. E. Johnson
    ARC/CP-64
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0064.pdf


    111. The natural frequencies of vibration of prismatic blades with particular reference to a 12 stage turbine

    R. Chaplin
    ARC/CP-95
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0095.pdf


    112. Wind tunnel tests on a 90 degrees apex delta wing of variable aspect ratio (sweepback 36.8 degrees) part 1 general stability part 2 measurements of downwash and effect of high lift devices

    J.G. Ross, R. Hills and R.C. Lock
    ARC/CP-83
    1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0083.pdf


    113. A comparison of calculated and measured base pressures of cylindrically based projectiles

    W. F. Cope
    ARC/CP-118
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0118.pdf


    114. A frost point hygrometer for supersonic wind tunnels

    D. Beastall and A. Winyard
    ARC/CP-106
    July, 1951

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0106.pdf


    115. A method for calculating pressure distributions on circular arc ogives at zero incidence at supersonic speeds, using the Prandtl-Meyer flow relations

    H. K. Zienkiewicz
    ARC/CP-114
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0114.pdf


    116. A note on shock tubes

    D. W. Holder
    ARC/CP-110
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0110.pdf


    117. A relaxation treatment of shock waves

    L. C. Woods
    ARC/CP-134
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0134.pdf


    118. A review and assessment of various formulae for turbulent skin friction in compressible flow

    R. J. Monaghan
    ARC/CP-142
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0142.pdf


    119. Air cooling methods for gas turbine combustion systems

    F. J. Bayley
    ARC/CP-133
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0133.pdf


    120. An analysis of the air flow through the nozzle blades of a single stage turbine

    I.H. Johnston
    ARC/CP-131
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0131.pdf


    121. An approximate method of deriving the transient response of a linear system from the frequency response

    C.A.A. Wass and E.G. Hayman
    ARC/CP-113
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0113.pdf


    122. Asymmetric Tailplane Loads Due to Sideslip

    Winfried Braun
    ARC/CP-119
    January, 1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0119.pdf


    123. Charts of the wave drag of wings at zero lift

    T. Lawrence
    ARC/CP-116
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0116.pdf


    124. Curves for estimating the wave drag of some bodies of revolution, based on exact and approximate theories

    L. E. Fraenkel
    ARC/CP-136
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0136.pdf


    125. Design of a right-angled bend with constant velocities at the walls

    A. S. Thom
    ARC/CP-135
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0135.pdf


    126. Effect of mean stress on the fatigue strength of D.T.D. 364 round bars with and without transverse holes

    G.M. Norris
    ARC/CP-120
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0120.pdf


    127. Growth of the turbulent wake close behind an aerofoil at incidence

    D. A. Spence
    ARC/CP-125
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0125.pdf


    128. Higher harmonics of flapping on the helicopter rotor

    W. Stewart
    ARC/CP-121
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0121.pdf


    129. Low speed wind tunnel investigation of tab hinge moment characteristics

    W.J.G. Trebble and J.F. Holford
    ARC/CP-112
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0112.pdf


    130. Measurement of lift, pitching moment and hinge moment on a two-dimensional RAE 102 aerofoil

    A. S. Batson
    ARC/CP-191
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0191.pdf


    131. Method for the determination of the pressure distribution over a finite thin wing at a steady low speed

    G. J. Hancock
    ARC/CP-128
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0128.pdf


    132. Note on the lift slope, and some other properties, of delta and swept-back wings

    E. F. Relf
    ARC/CP-127
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0127.pdf


    133. Pressure distribution and boundary layer investigations on 44 degree swept-back tapered wing part 1 three-dimensional tests on the wing part 2 two-dimensional pressure distribution tests on 10 per cent thick symmetrical aerofoil section

    Joseph Black
    ARC/CP-137
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0137.pdf


    134. Pressure error measurement using the formation method

    K.C. Levon
    ARC/CP-126
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0126.pdf


    135. Surface slopes and curvatures of the RAE 100-104 and other rooftop-type aerofoil sections

    J. Williams and Edna M. Love
    ARC/CP-129
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0129.pdf


    136. Tail plane loads and normal accelerations after an automatic control failure

    J.L. Reddaway
    ARC/CP-111
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0111.pdf


    137. Tests on an axial compressor with various stator blade staggers

    R.A. Jeffs, E.L. Hartley and P. Rooker
    ARC/CP-132
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0132.pdf


    138. The application of the polygon method to the calculation of the compressible subsonic flow round two-dimensional profiles

    L. C. Woods
    ARC/CP-115
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0115.pdf


    139. The definitions of the angles of incidence and of sideslip

    C.H.E. Warren
    ARC/CP-124
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0124.pdf


    140. The estimation of skin temperatures attained in high speed flight

    F.V. Davies and R.J. Monaghan
    ARC/CP-123
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0123.pdf


    141. The low speed performance of a helicopter

    A. L. Oliver
    ARC/CP-122
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0122.pdf


    142. The measurement of heat transfer and skin friction at supersonic speeds part 3 measurements of overall heat transfer and of the associated boundary layers on a flat plate at Ml = 2.43

    R. J. Monaghan and J. R. Cooke
    ARC/CP-139
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0139.pdf


    143. The measurement of heat transfer and skin friction at supersonic speeds part 4 tests on a flat plate at M = 2.82

    R. J. Monaghan and J. R. Cooke
    ARC/CP-140
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0140.pdf


    144. The performance of some typical turbo-jet engine exhaust systems, with particular reference to the effects of swirl

    P.F. Ashwood and P.J. Fletcher
    ARC/CP-130
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0130.pdf


    145. The theory of aerofoils with hinged flaps in two-dimensional compressible flow

    L. C. Woods
    ARC/CP-138
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0138.pdf


    146. The vibrations of a swept wing

    N.S. Heaps
    ARC/CP-141
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0141.pdf


    147. Wake survey and straingauge measurements on an inclined propeller in the R.A.E. 24 ft. tunnel part 1 wake survey

    J. G. Russell
    ARC/CP-117
    1953

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0117.pdf


    148. A method of computing subsonic and transonic plane flows

    C. S. Sinnot
    ARC/CP-173
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0173.pdf


    149. A note on the boundary layer and stalling characteristics of aerofoils

    D. D. Carrow
    ARC/CP-174
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0174.pdf


    150. A note on the development of sensitive pressure operated water contacts for use on seaplanes

    R. Parker
    ARC/CP-176
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0176.pdf


    151. A survey of scale effects on the hydrodynamic testing of seaplane models

    R. Parker
    ARC/CP-179
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0179.pdf


    152. A theoretical note on effusion cooled gas turbine blades

    R. Staniforth
    ARC/CP-165
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0165.pdf


    153. A variable inductance acceleration transducer

    H.K.P. Neubert
    ARC/CP-169
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0169.pdf


    154. Aerodynamic derivatives for a delta wing oscillating in elastic modes

    D.L. Woodcock
    ARC/CP-170
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0170.pdf


    155. An analysis of N.A.C.A. helicopter reports

    R. N. Liptrot
    ARC/CP-183
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0183.pdf


    156. An investigation into the pitot rake method of measuring turbo jet engine thrust in flight

    J. Stephenson, R. T. Shields and D. W. Bottle
    ARC/CP-143
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0143.pdf


    157. An investigation into the rolling power and aileron reversal characteristics of swept wings

    A. V. Coles and R. J. Margetts
    ARC/CP-159
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0159.pdf


    158. Analysis of flight measurements on the airborne path during take-off

    W. R. Buckingham and D. Lean
    ARC/CP-156
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0156.pdf


    159. Calibration of the R.A.E. No. 18 (9" x 9") supersonic wind tunnel part 1 preliminary investigations

    W.T. Lord and D. Beastall
    ARC/CP-162
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0162.pdf


    160. Calibration of the R.A.E. No. 18 (9" x 9") Supersonic Wind Tunnel. Part II:- Tests at Atmospheric Stagnation Pressure

    W.T. Lord, G.K. Hunt, R.J. Pallant, and J. Turner
    ARC/CP-163
    September, 1953

    This report presents distributions of Mach number in the empty working section of the R.A.E. No. 18 (9" x 9") Supersonic Wind Tunnel at nominal Mach numbers of 1.4, 1.5, 1.6, 1.8 and 1.9, for condensation-free flow at atmospheric stagnation pressure and at a stagnation temperature cf 35°C. The results confirm that the accuracy of the tests is of the order predicted in Part I. The mean measured Mach numbers are 1.41, 1.51 1.61, 1.81 and 1.91 when calculated from values of pitot and stagnation pressures. The major contributions to the non-uniformity of the flow are from the disturbances which arise from the junctions of the windows with the side walls of the tunnel; these disturbances are of the order of + or -0.015 in Mach number, whilst the maximum gradual variations in the flow caused by other sources are of the order of + or -0.010. An indication cf the boundaries of the working section for each Mach number is given. Note (August, 1953) Since the accounts of the calibration contained in Parts I and II were written (Part I: December, 1951 Part II: March, 1952), the tunnel equipment has been greatly improved and its limitations are no longer as severe as those described here; the improvements do not invalidate the present results, but no further detailed calibration measurements have been made.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0163.pdf


    161. Criteria for condensation free flow in the R.A.E. no. 18 (9" x 9") supersonic tunnel

    D. J. Raney and D. Beastall
    ARC/CP-164
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0164.pdf


    162. Development of an air mass-flow rate meter

    W.J.G. Cox
    ARC/CP-230
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0230.pdf


    163. Experiments at M = 1.8 on bodies of revolution having ogival heads

    H. K. Zienkiewicz et al
    ARC/CP-148
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0148.pdf


    164. Factors influencing the optimum aerodynamic design of cooled turbines

    G. F. C. Rogers
    ARC/CP-155
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0155.pdf


    165. List of current papers published by the Aeronautical Research Council numbers 101-150


    ARC/CP-150
    March, 1954

    This paper lists fifty titles which have been published in the CP Series of the Aeronautical Research Council.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0150.pdf


    166. Note on an application of the tilting plate method of Mach number variation for wind tunnel tests at low supersonic speeds

    J. Seddon and L. Haverty
    ARC/CP-168
    March, 1953

    When a flat plate mounted in the working section of a supersonic wind tunnel is inclined at an angle to the stream, there exists a region above the surface of the plate in which the Mach number is constant and different from the main stream value. In limited circumstances this region may be used as the test section and it is possible, by varying the angle of the plate, to obtain a continuous variation of test Mach number with the one fixed tunnel nozzle. This method of Mach number control can be particularly useful for making wind tunnel tests near M = 1.0.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0168.pdf


    167. Note on the effect of thickness and aspect ratio on the damping of pitching oscillations of rectangular wings moving at supersonic speeds

    W. E. A. Acum
    ARC/CP-151
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0151.pdf


    168. Schlieren methods for observing high-speed flows

    D. W. Holder and R. J. North
    ARC/CP-167
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0167.pdf


    169. Stationary rig experiments on the heat extracting power of closed thermosyphon cooling holes

    H. W. Hahnemann
    ARC/CP-152
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0152.pdf


    170. Tabulation of the blasius function with blowing and suction

    H. W. Emmons and D. C. Leigh
    ARC/CP-157
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0157.pdf


    171. Tests on a swept-back wing and body with endplates and wing tip tanks in the compressed air tunnel

    C. Salter, and R. Jones
    ARC/CP-196
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0196.pdf


    172. The application of camber and twist to swept wings in incompressible flow

    G.G. Brebner
    ARC/CP-171
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0171.pdf


    173. The effect of compressibility on elevator flutter

    D. E. Williams
    ARC/CP-185
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0185.pdf


    174. The effect of inlet conditions on the flow in annular diffusers

    I. H. Johnston
    ARC/CP-178
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0178.pdf


    175. The effect of rolling on fin-and-rudder loads in yawing manoeuvres

    D.R. Puttock
    ARC/CP-153
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0153.pdf


    176. The influence of surface waves on the stability of a laminar boundary layer with uniform suction

    D. A. Spence and D. G. Randall
    ARC/CP-161
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0161.pdf


    177. The M.A.E.E. recording accelerometer

    D. M. Ridland and R. Parker
    ARC/CP-177
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0177.pdf


    178. The manufacture of aerofoil models by tangent plane milling

    R. S. Marriner
    ARC/CP-166
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0166.pdf


    179. The measurement of position error at high speeds and altitude by means of a trailing static head

    K.W. Smith
    ARC/CP-160
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0160.pdf


    180. The performance of a multi-engine helicopter following failure of one engine during take-off or landing

    A.L. Oliver
    ARC/CP-175
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0175.pdf


    181. The Performance of the 108 Compressor Fitted with Low Stagger Free Vortex Blading

    D. V. Foster
    ARC/CP-144
    June, 1952

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0144.pdf


    182. The rapid, accurate prediction of pressure on non-lifting ogival heads of arbitrary shape, at supersonic speeds

    B. W. Bolton-Shaw and H. K. Zienkiewicz
    ARC/CP-154
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0154.pdf


    183. The technique of flutter calculations

    H. Templeton
    ARC/CP-172
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0172.pdf


    184. The theoretical interference velocity on the axis of a two-dimensional wind tunnel with slotted walls

    R. C. Tomlinson
    ARC/CP-181
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0181.pdf


    185. The thermodynamics of frictional resisted adiabatic flow of gases through ducts of constant and varying cross section

    W. R. Thomson
    ARC/CP-158
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0158.pdf


    186. Theoretical load distributions on wings with cylindrical bodies at the tips

    D.E. Hartley
    ARC/CP-147
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0147.pdf


    187. Unsteady cavitating flow past curved obstacles

    L. C. Woods
    ARC/CP-149
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0149.pdf


    188. Vibration and flutter of aircraft aerials

    W. H. Johnson
    ARC/CP-146
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0146.pdf


    189. Zero lift drag measurements on swept wings at transonic and supersonic speeds using the ground-launched rocket-boosted model technique

    T. Lawrence, and C. Kell
    ARC/CP-145
    1954

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0145.pdf


    190. A criterion for the prediction of the recovery characteristics of spinning aircraft

    T. H. Kerr
    ARC/CP-195
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0195.pdf


    191. A note on the sound from weak disturbances of a normal shock wave

    Alan Powell
    ARC/CP-194
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0194.pdf


    192. A technique for the measurement of pressure distribution on oscillating aerofoils, with results for a rectangular wing of aspect ratio 3.3

    W. G. Molyneux and F. Ruddlesden
    ARC/CP-233
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0233.pdf


    193. A theoretical investigation of the factors affecting stalling flutter of compressor blades

    A. D. S. Carter
    ARC/CP-265
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0265.pdf


    194. Additional data on surface slopes of the RAE 100 - 104 aerofoil sections

    Edna M. Love and J. Williams
    ARC/CP-252
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0252.pdf


    195. An analysis of aerodynamic data on blowing over trailing edge flaps for increasing lift

    J. Williams
    ARC/CP-209
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0209.pdf


    196. An automatic self-balancing capsule manometer

    G. F. Midwood, R. W. Hayward
    ARC/CP-231
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0231.pdf


    197. Approximate wall corrections for an oscillating swept wing in a wind tunnel of closed circular section

    W. E. A. Acum and H. C. Garner
    ARC/CP-184
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0184.pdf


    198. Compressor cascade flutter tests 20 degrees camber blades, medium and high stagger cascades

    D. A. Kilpatrick and J. Ritchie
    ARC/CP-187
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0187.pdf


    199. Correlated fatigue data for aircraft structural joints

    R.B. Heywood
    ARC/CP-227
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0227.pdf


    200. Experiments on a slotted-wall working section in a wind tunnel

    F. Vandrey and K. Wieghardt
    ARC/CP-206
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0206.pdf


    201. Flutter calculations on a resonance model delta wing

    H. Hall
    ARC/CP-260
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0260.pdf


    202. Further experiments with a slotted-wall test section

    F. Vandrey
    ARC/CP-207
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0207.pdf


    203. Investigation of high length/beam ratio seaplane hulls with high beam loadings hydrodynamic stability part 1 techniques and presentation of results of model tests

    D. M. Ridland, J. K. Friswell, A. G. Kurn
    ARC/CP-201
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0201.pdf


    204. Investigation of high length/beam ratio seaplane hulls with high beam loadings hydrodynamic stability part 10 the effect of afterbody length on stability and spray characteristics

    D.M. Ridland
    ARC/CP-204
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0204.pdf


    205. Investigation of high length/beam ratio seaplane hulls with high beam loadings hydrodynamic stability part 2 the effect of changes in the mass, moment of inertia and radius of gyration on longitudinal stability limits

    J. K. Friswell, A. Kurn, D.M. Ridland
    ARC/CP-202
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0202.pdf


    206. Investigation of high length/beam ratio seaplane hulls with high beam loadings hydrodynamic stability Part 21 some notes on the effect of waves on longitudinal stability characteristics

    D. M. Ridland
    ARC/CP-237
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0237.pdf


    207. Investigation of high length/beam ratio seaplane hulls with high beam loadings hydrodynamic stability part 6 the effect of forebody warp on stability and spray characteristics

    D. M. Ridland
    ARC/CP-203
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0203.pdf


    208. Investigation of the fatigue of extruded tubular booms

    W.A.P. Fisher and H. Yeomans
    ARC/CP-234
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0234.pdf


    209. List of current papers published by the Aeronautical Research Council (numbers 151-200)

    Aeronautical Research Council
    ARC/CP-200
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0200.pdf


    210. Load diffusion in plastic structures

    L.M. Tucker and R.B. Twiss
    ARC/CP-186
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0186.pdf


    211. Measurements of pitching moment derivatives for a series of rectangular wings at low wind speeds

    P. R. Guyett and D. E. G. Poulter
    ARC/CP-249
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0249.pdf


    212. Methods for reducing seaplane take-off distances to standard conditions

    J. A. Hamilton
    ARC/CP-219
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0219.pdf


    213. Methods of determination and of fixing boundary layer transition on wind tunnel models at supersonic speeds

    K. G. Winter, J. B. Scott-Wilson, F. V. Davies
    ARC/CP-212
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0212.pdf


    214. Models for aero-elastic investigations

    H. Templeton
    ARC/CP-255
    November, 1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0255.pdf


    215. Note on the flow near the tail of a two-dimensional aerofoil moving at a free-stream mach number close to unity

    D. W. Holder
    ARC/CP-188
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0188.pdf


    216. On the laminar boundary layer separation from the leading edge of a thin aerofoil

    P. R. Owen and L. Klanfer
    ARC/CP-220
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0220.pdf


    217. Optical characteristics of laminated camera windows

    A.C. Marchant and B.M. Mathieson
    ARC/CP-210
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0210.pdf


    218. Pressure distributions illustrating flow reattachment behind a forward mounted flap

    E.C. Maskell
    ARC/CP-211
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0211.pdf


    219. Pressure distributions: axially symmetric bodies in oblique flow

    I. J. Campbell and R.G. Lewis
    ARC/CP-213
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0213.pdf


    220. Pressure-cabin design a discussion of some of the structural problems involved, with suggestions for their solution

    D. Williams
    ARC/CP-226
    March, 1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0226.pdf


    221. Report of the definitions panel on the definitions of the thrust of a jet engine and of the Internal Drag of a ducted body

    Aeronautical Research Council
    ARC/CP-190
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0190.pdf


    222. Requirements for uniformity of flow in supersonic wind tunnels

    D. E. Morris and K. G. Winter
    ARC/CP-197
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0197.pdf


    223. Shadowgraphs of model projectiles fired at high mach numbers and near M = 1 in the N.P.L. Ballistic range

    W. F. Cope
    ARC/CP-189
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0189.pdf


    224. Some notes on the calculation of pressure pick-up sensitivity and the conditions for maximum sensitivity and the development of a miniature pressure pick-up

    J. K. Friswell
    ARC/CP-199
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0199.pdf


    225. Some visual observations of the flow over a swept-back wing in a water tunnel, with particular reference to high incidences

    M. C. Lambourne and P. S. Pusey
    ARC/CP-192
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0192.pdf


    226. Some work on tension pads for structural tests

    J.K. Oaks and P.B. Hovell
    ARC/CP-238
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0238.pdf


    227. Stress considerations in the design of pressurised shells

    E. H. Mansfield
    ARC/CP-217
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0217.pdf


    228. The buckling under longitudinal compression of a simply supported panel that changes in thickness across the width

    E. C. Capey
    ARC/CP-235
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0235.pdf


    229. The influence of pre-loading on the fatigue life of aircraft components and structures

    R. B. Heywood
    ARC/CP-232
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0232.pdf


    230. The interaction between shock waves and boundary layers with a note on the effects of the interaction on the performance of supersonic intakes

    D. W. Holder et al
    ARC/CP-180
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0180.pdf


    231. The laminar boundary-layer with distributed suction on an infinite yawed cylinder

    K. D. P. Sinha
    ARC/CP-214
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0214.pdf


    232. The strength of tubes under uniform external pressure

    P.C. Cleaver
    ARC/CP-253
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0253.pdf


    233. The torsional vibrations of a class of thin, tapered, solid wings

    Elizabeth A. Frost
    ARC/CP-218
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0218.pdf


    234. The use of quartz in the manufacture of small diameter pitot tubes

    J.R. Cooke
    ARC/CP-193
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0193.pdf


    235. Theory of the broad-bladed propeller

    G. I. Ginzel
    ARC/CP-208
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0208.pdf


    236. Wide range amplifier for turbulence measurements with adjustable upper frequency limit

    H. Schuh, and D. Walker
    ARC/CP-198
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0198.pdf


    237. Wind tunnel tests on a 6 ft diameter helicopter rotor

    T. B. Owen, R. Fail and R. C. W. Eyre
    ARC/CP-216
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0216.pdf


    238. Wind tunnel tests on antisymmetric flutter of a delta wing with rolling body freedom

    D. R. Gaukroger and D. Nixon
    ARC/CP-259
    1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0259.pdf


    239. A constructional method for minimising the hazard of catastrophic failure in a pressure-cabin

    D. Williams
    ARC/CP-286
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0286.pdf


    240. A corrected speed tachoscope

    R. Staniforth
    ARC/CP-224
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0224.pdf


    241. A flight investigation of the wake behind a meteor aircraft, with some theoretical analysis

    D. R. Andrews
    ARC/CP-282
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0282.pdf


    242. A note on derivative apparatus for the N.P.L. 9.5-inch high speed tunnel

    J. B. Bratt
    ARC/CP-269
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0269.pdf


    243. Aerodynamic derivatives for two cropped delta wings and one arrowhead wing oscillating in distortion modes

    D. L. Woodcock
    ARC/CP-268
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0268.pdf


    244. An experimental investigation of Meksyn's transonic inviscid flow theory

    C. S. Sinnott
    ARC/CP-302
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0302.pdf


    245. An experimental investigation of the blade vibratory stresses in a single stage compressor

    A. D. S. Carter et al
    ARC/CP-266
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0266.pdf


    246. An index of mathematical tables for shock-tube flow

    B. D. Henshall
    ARC/CP-292
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0292.pdf


    247. An Investigation of High Altitude Cruising Conditions for Turbo-jet Aircraft

    R. T. Shields, J. Stephenson and I. E. Utting
    ARC/CP-215
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0215.pdf


    248. Base pressures in supersonic flow

    G. E. Gadd, D. W. Holder and J. D. Regan
    ARC/CP-271
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0271.pdf


    249. Boundary layer measurements on 10 degrees and 20 degrees cones at M = 2.45 and zero heat transfer

    F. V. Davies and J. R. Cooke
    ARC/CP-264
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0264.pdf


    250. Boundary layer separation in two-dimensional supersonic flow

    G. E. Gadd and D. W. Holder
    ARC/CP-270
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0270.pdf


    251. Calibration of the flow in the working section of the 3 ft x 3 ft tunnel, National Aeronautical Establishment

    D. E. Morris
    ARC/CP-261
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0261.pdf


    252. Compressor cascade flutter tests part 2 40 degrees camber blades, low and medium stagger cascades

    D. A. Kilpatrick and J. Ritchie
    ARC/CP-296
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0296.pdf


    253. Factors affecting the performance of the nozzle of a hypersonic shock tube

    B. D. Henshall and G. E. Gadd
    ARC/CP-293
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0293.pdf


    254. Fatigue loadings in flight - loads in the fuselage and nose undercarriage of a varsity

    E. W. Wells
    ARC/CP-287
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0287.pdf


    255. Fatigue loadings in flight - loads in the wing of a varsity

    Anne Burns
    ARC/CP-285
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0285.pdf


    256. Fatigue loadings in flight loads in the tailplane and fin of a varsity

    Anne Burns
    ARC/CP-256
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0256.pdf


    257. Fin-and-rudder loads in a yawing manoeuvre effect of direct and power assisted rudder movement

    D. R. Puttock
    ARC/CP-301
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0301.pdf


    258. Flow direction measurements in supersonic wind tunnels

    D. J. Raney
    ARC/CP-262
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0262.pdf


    259. Flutter calculations on a rudder with trailing-edge spoiler

    Ll. T. Niblett
    ARC/CP-277
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0277.pdf


    260. Full scale spinning tests on the percival provost mk.1 including the inverted spin

    T. H. Kerr
    ARC/CP-240
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0240.pdf


    261. Heat transfer to turbine blades

    S.J. Andrews and P.C. Bradley
    ARC/CP-294
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0294.pdf


    262. Ill-conditioned flutter equations and their improvement for simulator use

    E.G. Broadbent
    ARC/CP-298
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0298.pdf


    263. Impact measurements on a large model of a representative landplane fuselage on water

    J.E.Allen
    ARC/CP-283
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0283.pdf


    264. Investigation of high length/beam ratio seaplane hulls with high beam loadings hydrodynamic stability Part 13 the effect of afterbody angle on stability and spray characteristics

    D. M. Ridland
    ARC/CP-236
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0236.pdf


    265. List of current papers published by the Aeronautical Research Council (numbers 201-250)

    Aeronautical Research Council
    ARC/CP-250
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0250.pdf


    266. Loading conditions following an automatic pilot failure (elevator channel)

    D. R. Puttock
    ARC/CP-243
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0243.pdf


    267. Loading conditions following an automatic pilot failure (rudder channel)

    D.R. Puttock
    ARC/CP-242
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0242.pdf


    268. Low speed static and fluctuating pressure distributions on a cylindrical body with a square flat plate airbrake

    T. B. Owen
    ARC/CP-288
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0288.pdf


    269. Low speed wind tunnel calibration of a mark 9A pitot-static head

    J. E. Nethaway
    ARC/CP-244
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0244.pdf


    270. Measurement of lift, pitching moment and hinge moment on a two-dimensional cusped RAE.102 aerofoil

    A. S. Batson
    ARC/CP-272
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0272.pdf


    271. Note on the effect of size and position of end plates on the lift of a rectangular wing in a wind tunnel

    A. S. Halliday and D. K. Cox
    ARC/CP-305
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0305.pdf


    272. On the stability of a laminar wake

    C. H. McKoen
    ARC/CP-303
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0303.pdf


    273. Optimum designs for reinforced circular holes

    E. H. Mansfield
    ARC/CP-239
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0239.pdf


    274. Preliminary Low Speed Wind Tunnel Tests on Flat Plates and Air Brakes: Flow, Vibration and Balance Measurements

    R. Fail, T. B. Owen and R. C. W. Eyre
    ARC/CP-251
    January, 1955

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0251.pdf


    275. Relative accuracy of deflections and bending moments (or stresses) derived by the method of RAE report no. structures 168

    D. Williams
    ARC/CP-254
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0254.pdf


    276. Report of the first year's flying on the development of flight testing techniques for finding and measuring natural icing conditions

    G. C. Abel
    ARC/CP-221
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0221.pdf


    277. Report of the pressure panel on the definitions of quantities having the dimensions of pressure

    Aeronautical Research Council
    ARC/CP-281
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0281.pdf


    278. Report of the second year's flying on the development of flight testing techniques for finding and measuring natural icing conditions

    G. C. Abel
    ARC/CP-222
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0222.pdf


    279. Report of the third year's flying on the development of flight testing techniques for finding and measuring natural icing conditions

    G. C. Abel
    ARC/CP-223
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0223.pdf


    280. Saunders-Roe princess flying boat G-alun air and water handling tests

    Marine Aircraft Experimental Establishment
    ARC/CP-257
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0257.pdf


    281. Saunders-Roe princess flying boat G-alun air and water performance tests

    Aeronautical Research Council
    ARC/CP-279
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0279.pdf


    282. Saunders-Roe princess flying boat G-alun engineering appraisal

    Aeronautical Research Council
    ARC/CP-280
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0280.pdf


    283. Some advantages and disadvantages of variable and non-linear gearing between the pilot's control and the control surface

    D. A. Lang
    ARC/CP-263
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0263.pdf


    284. Some experiments on an effusion cooled turbine nozzle blade

    S. J. Andrews, H. Ogden, Jane Marshall
    ARC/CP-267
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0267.pdf


    285. Some fatigue characteristics of a two spar light alloy structure (meteor 4 tailplane)

    K. D. Raithby and Jennifer Longson
    ARC/CP-258
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0258.pdf


    286. Some notes on the flow durations occurring in hypersonic shock tubes

    B. D. Henshall
    ARC/CP-290
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0290.pdf


    287. Some Tests on the Spread of Velocity in a Cold Jet Discharging with Excess Pressure from a Sonic Exit into Still Air

    J. Seddon and L. Haverty
    ARC/CP-246
    November 1955

    The spread of the half-velocity circle in a jet discharging with excess pressure from a length of parallel pipe into still air has been examined over the range 40 to 200 diameters from the exit. Jet pressure ratios (outside static pressure + jet total pressure) were from 0.479 to 0.042, corresponding to isentropic Mach numbers from 1.08 to 2.72.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0246.pdf


    288. Tests of Humidity Effects on Flow in a Wind Tunnel at Mach Numbers between 2.48 and 4

    R. J. Monaghan M.A.
    ARC/CP-247
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0247.pdf


    289. Tests on rough surfaced compressor blading

    R. C. Turner and Hazel P. Hughes
    ARC/CP-306
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0306.pdf


    290. The development of an improved diffuser for a 3 ft x 3 ft tunnel

    J. B. Scott-Wilson and D. I. T. P. Llewelyn-Davies
    ARC/CP-308
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0308.pdf


    291. The direction of flow in the laminar boundary layer on an infinite yawed cylinder

    K. D. P. Sinha
    ARC/CP-295
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0295.pdf


    292. The effect of lacing wire on axial compressor stage performance at low speeds

    S. J. Andrews and H. Ogden
    ARC/CP-225
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0225.pdf


    293. The effects of convex surface curvature on boundary layer separation in supersonic flow

    G. E. Gadd
    ARC/CP-289
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0289.pdf


    294. The hot-wire anemometer for turbulence measurements part 1

    B. Wise
    ARC/CP-273
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0273.pdf


    295. The hot-wire anemometer for turbulence measurements part 3

    B. Wise, and D. L. Schultz
    ARC/CP-275
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0275.pdf


    296. The hot-wire anemometer for turbulence measurements part 4

    B. Wise, and D. L. Schultz
    ARC/CP-276
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0276.pdf


    297. The Hot-Wire Anemometer for Turbulence Measurements Part II

    B. Wise and D. R. Stewart
    ARC/CP-274
    2th September, 1951

    An account is given of some experimental work undertaken to test the theory of operation of a hot-wire anemometer with radio-frequency heating, which has been given in a previous paper.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0274.pdf


    298. The measurement of absorptivity and reflectivity

    E. T. de la Perrelle and H. Herbert
    ARC/CP-601
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0601.pdf


    299. The secondary flow in compressor blades at high negative incidences

    W. D. Armstrong
    ARC/CP-297
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0297.pdf


    300. The theoretical wave drag of open-nose axisymmetrical forebodies with varying fineness ratio, area ratio and nose angle

    J.H. Willis and D.G. Randall
    ARC/CP-245
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0245.pdf


    301. The use of multiple diaphragms in shock tubes

    B. D. Henshall
    ARC/CP-291
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0291.pdf


    302. Towing tank tests to determine the water drag of the hull of a jet-propelled flying boat fighter (spec.E.6/44) and comparison with full scale measurements

    R.V. Gigg, A.G. Kurn, J.K. Friswell
    ARC/CP-284
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0284.pdf


    303. Transient thermal stress in a flat plate due to non-uniform heat transfer across one surface

    N. S. Heaps
    ARC/CP-299
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0299.pdf


    304. Turbulence encountered by comet 1 aircraft

    J.R. Heath-Smith
    ARC/CP-248
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0248.pdf


    305. Turbulent diffuser flow

    B. S. Stratford
    ARC/CP-307
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0307.pdf


    306. Variations in the strength of aluminium alloy sheet

    D.T. Jones
    ARC/CP-229
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0229.pdf


    307. Velocity calculations by conformal mapping for two-dimensional aerofoils

    D. A. Spence and N.A. Routledge
    ARC/CP-241
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0241.pdf


    308. Vibration and flutter flight testing

    M. O. W. Wolfe
    ARC/CP-310
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0310.pdf


    309. Wake survey and Straingauge measurements on an inclined propeller in the R.A.E. 24ft tunnel part 2 comparison of measured and calculated 1P stresses

    R. Doust and E. J. Hellier
    ARC/CP-228
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0228.pdf


    310. Water tunnel boundary effects on axially symmetric fully developed cavities

    I. J. Campbell and G. E. Thomas
    ARC/CP-278
    1956

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0278.pdf


    311. A geared flywheel balance arrangement for the prevention of control surface flutter

    W. G. Molyneux
    ARC/CP-365
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0365.pdf


    312. A generalisation of the Nyquist stability criterion with particular reference to phasing error

    R. H. Merson
    ARC/CP-330
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0330.pdf


    313. A graphical method of predicting the off design performance of a compressor stage

    J. F. Louis and J. H. Horlock
    ARC/CP-320
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0320.pdf


    314. A note on some integrals in aerodynamics

    D.E. Williams
    ARC/CP-364
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0364.pdf


    315. A note on turbulent boundary-layer allowances in supersonic nozzle design

    E. W. E. Rogers and B. M. Davis
    ARC/CP-333
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0333.pdf


    316. A review of the problems of aircraft wheel braking on wet surfaces and a description of a method of artificially wetting runways for test purposes

    H. J. Keyes
    ARC/CP-592
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0592.pdf


    317. A review of theoretical work relevant to the problem of heat transfer effects on laminar separation

    G. E. Gadd
    ARC/CP-331
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0331.pdf


    318. Actuator disc theories applied to the design of axial compressors

    A. D. Carmichael and J. H. Horlock
    ARC/CP-315
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0315.pdf


    319. An analogue computer for convective heating problems

    H. G. R. Robinson
    ARC/CP-374
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0374.pdf


    320. An experimental introduction to the jet flap

    N. A. Dimmock
    ARC/CP-344
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0344.pdf


    321. An experimental verification of the theoretical conclusions of R.A.E. technical note no. structures 156 (A.R.C., C.P. no. 286) "a constructional method for minimising the no. structures 156 (A.R.C., C.P. no. 286) "a constructional method for minimising th

    D. Williams
    ARC/CP-357
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0357.pdf


    322. Assessment of the possibility of using suction to inhibit cavitation on cylindrical sections

    G. E. Thomas
    ARC/CP-362
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0362.pdf


    323. Atmospheric turbulence encountered by Hermes aircraft

    J.R. Heath-Smith
    ARC/CP-334
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0334.pdf


    324. Brief description of the Royal Aircraft Establishment intermittent supersonic wind tunnel plant

    K. G. Winter
    ARC/CP-336
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0336.pdf


    325. Charts of the theoretical wave drag of wings at zero-lift

    R. A. Bishop and E. G. Cane
    ARC/CP-313
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0313.pdf


    326. Curves suitable for families of aerofoils with variable maximum thickness position, nose radius, camber and nose droop

    L. H. tanner
    ARC/CP-358
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0358.pdf


    327. Direct stress fatigue tests on redux-bonded and riveted double strap joints in 10 S.W.G. aluminium alloy sheet

    S. Kelsey and J. B. Spooner
    ARC/CP-353
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0353.pdf


    328. Effects of elevator circuit stiffness on the loading conditions in longitudinal manoeuvres

    D.R. Puttock
    ARC/CP-354
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0354.pdf


    329. Experimental investigation of the pressure distribution at the centre-section of a sweptback wing at high subsonic speeds

    T. E. B. Bateman and A. J. Lawrence
    ARC/CP-367
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0367.pdf


    330. Experiments on the growth of vortices in turbulent flow

    I. M. Titchener and A. J. Taylor-Russell
    ARC/CP-316
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0316.pdf


    331. Fatigue loadings in flight - loads in the tailplane of a comet 1

    Anne Burns
    ARC/CP-363
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0363.pdf


    332. Flutter calculations on a supersonic aircraft wing

    Ll. T. Niblett
    ARC/CP-328
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0328.pdf


    333. Flutter prediction in practice

    E. G. Broadbent
    ARC/CP-373
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0373.pdf


    334. Formulae and approximations for aerodynamic heating rates in high speed flight

    R. J. Monaghan
    ARC/CP-360
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0360.pdf


    335. Full scale measurement of impact loads on a large flying boat (sunderland MK. 5) part 3 data for impacts on main step

    R. Parker
    ARC/CP-340
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0340.pdf


    336. Full scale measurements of impact loads on a large flying boat (sunderland 5) part 4 data for impacts on the afterbody

    R. Parker
    ARC/CP-341
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0341.pdf


    337. Full scale measurements of impact loads on a large flying boat (Sunderland MK.5) part 5 results of rough water tests

    R. Parker, J.K. Friswell
    ARC/CP-342
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0342.pdf


    338. Instability in a slotted wall tunnel

    J. L. King, P. Boyle and J. B. Ogle
    ARC/CP-343
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0343.pdf


    339. Instrumentation used in measurement of the three dimensional flow in an axial flow compressor

    J. H. Horlock
    ARC/CP-321
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0321.pdf


    340. Investigation of high length/beam ratio seaplane hulls with high beam loadings hydrodynamic stability part 14 the effect of a tailored afterbody on stability and spray characteristics with test data on model J

    D. M. Ridland
    ARC/CP-351
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0351.pdf


    341. Investigation of high length/beam ratio seaplane hulls with high beam loadings hydrodynamic stability part 19 the interaction of the effects of forebody warp, afterbody length and afterbody angle on longitudinal stability characteristics

    J. K. Friswell
    ARC/CP-352
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0352.pdf


    342. Investigation of high length/beam ratio seaplane hulls with high beam loadings hydrodynamic stability part 20 the effect of slipstream on stability and spray characteristics

    D. M. Ridland
    ARC/CP-349
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0349.pdf


    343. List of current papers published for the Aeronautical Research Council (numbers 251-300)

    Aeronautical Research Council
    ARC/CP-300
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0300.pdf


    344. List of current papers published for the Aeronautical Research Council numbers 301-350


    ARC/CP-350
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0350.pdf


    345. Loads on a model during starting and stopping of an intermittent supersonic wind tunnel

    K. G. Winter and C. S. Brown
    ARC/CP-335
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0335.pdf


    346. Low speed wind tunnel tests on perforated square flat plates normal to the airstream drag and velocity fluctuation measurements

    B. G. de Bray
    ARC/CP-323
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0323.pdf


    347. Measurements of the thrust produced by convergent-divergent nozzles at pressure ratios up to 20

    P. F. Ashwood, G. W. Crosse and Jean E. Goddard
    ARC/CP-326
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0326.pdf


    348. Notation for rotorcraft work

    A. Armitage
    ARC/CP-314
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0314.pdf


    349. Nozzle and contraction shapes of the R.A.E. 3 ft x 3 ft supersonic wind tunnel

    A. Stanbrook
    ARC/CP-375
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0375.pdf


    350. On a type of air lubricated journal bearing

    G.L. Shires
    ARC/CP-318
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0318.pdf


    351. Preliminary analysis for a jet flap system in two-dimensional inviscid flow

    E. C. Maskell and S. B. Gates
    ARC/CP-359
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0359.pdf


    352. Problems in computation of aerodynamic loading on oscillating lifting surfaces

    H. C. Garner, and W. E. A. Acum
    ARC/CP-309
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0309.pdf


    353. Results of a flight investigation on clear air turbulence at low altitude using a meteor Mk.7 aircraft

    R. M. Allan
    ARC/CP-329
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0329.pdf


    354. Some aspects of compressor stage design

    J. F. Louis and J. H. Horlock
    ARC/CP-319
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0319.pdf


    355. Some further jet flap experiments

    N. A. Dimmock
    ARC/CP-345
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0345.pdf


    356. Some notes on shock-wave boundary-layer interactions, and on the effect of suction on the separation of laminar boundary layers

    K. N. C. Bray
    ARC/CP-332
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0332.pdf


    357. Substantiation of safe fatigue life for rotorcraft

    W. A. P. Fisher
    ARC/CP-317
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0317.pdf


    358. Supports for vibration isolation

    W. G. Molyneux
    ARC/CP-322
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0322.pdf


    359. Tables of characteristics slopes for use in the design of nozzles for supersonic wind tunnels

    K. G. Winter
    ARC/CP-337
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0337.pdf


    360. The calculation of the paths of vortices from a system of vortex generators, and a comparison with experiment

    J. P. Jones
    ARC/CP-361
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0361.pdf


    361. The deformation of a long swept wing with chordwise variation of the thickness

    E.C. Capey
    ARC/CP-348
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0348.pdf


    362. The determination of aerodynamic coefficients from flutter test data

    W. G. Molyneux
    ARC/CP-347
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0347.pdf


    363. The effect of heat transfer on interactions involving laminar boundary layers

    K. N. C. Bray
    ARC/CP-339
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0339.pdf


    364. The flow through short straight pipes in a compressible viscous stream

    J. Seddon
    ARC/CP-355
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0355.pdf


    365. The influence of design pressure ratio and divergence angle on the thrust of convergent-divergent propelling nozzles

    P. F. Ashwood and D. G. Higgins
    ARC/CP-325
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0325.pdf


    366. The influence of pressure ratio and divergence angle on the shock position in two dimensional, over-expanded, convergent-divergent nozzles

    P. F. Ashwood and G. W. Crosse
    ARC/CP-327
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0327.pdf


    367. The numerical integration of the laminar compressible boundary layer equations, with special reference to the position of separation when the wall is cooled

    G. E. Gadd
    ARC/CP-312
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0312.pdf


    368. The operation of the N.P.L. 18 inches x 14 inches wind tunnel in the transonic speed range

    I. M. Hall
    ARC/CP-338
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0338.pdf


    369. The use of an araldite coated iron casting as a liner for a supersonic wind tunnel

    C. S. Brown and K. G. Winter
    ARC/CP-346
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0346.pdf


    370. The variation of gust frequency with gust velocity and altitude

    N. I. Bullen
    ARC/CP-324
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0324.pdf


    371. Three-dimensional wind-tunnel tests of a 30 degrees jet flap model

    J. Williams and A. J. Alexander
    ARC/CP-304
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0304.pdf


    372. Turbulence encountered by Viking aircraft over Europe

    J. R. Heath-Smith
    ARC/CP-311
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0311.pdf


    373. Turbulence measurements in supersonic flow with the hot-wire anemometer

    B. Wise and D. L. Schultz
    ARC/CP-366
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0366.pdf


    374. Ultrasonic relaxation and attenuation in freons, in relation to their use in supersonic wind tunnels

    Y. Miyahara and E. G. Richardson
    ARC/CP-356
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0356.pdf


    375. Wing flow measurements of the damping in pitch derivative of a 45 degrees delta wing-body combination and with a tailplane in two positions

    R. Rose
    ARC/CP-402
    1957

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0402.pdf


    376. A deuce programme for the solution of two-dimensional heat-flow problems

    K. I. McKenzie
    ARC/CP-417
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0417.pdf


    377. A flight technique for the measurement of thrust boundaries and of drag due to lift

    H. D. Rylands
    ARC/CP-405
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0405.pdf


    378. A method of calculating the effect of one helicopter rotor upon another

    I. C. Cheeseman
    ARC/CP-406
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0406.pdf


    379. A note on the interpretation of base pressure measurements in supersonic flows

    R. C. Hastings
    ARC/CP-409
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0409.pdf


    380. A roll-balance free-flight test vehicle for the measurement of aileron rolling power and roll damping at M = 0.8 to 2.5

    K. J. Turner
    ARC/CP-679
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0679.pdf


    381. A shock-expansion theory applicable to wings with attached shock waves

    L.M. Sheppard and K.D. Thomson
    ARC/CP-392
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0392.pdf


    382. A simplified form of the auxiliary equation for use in the calculation of turbulent boundary layers

    T. J. Black
    ARC/CP-370
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0370.pdf


    383. A technique for improving the predictions of linearised theory on the drag of straight-edged wings

    D. G. Randall
    ARC/CP-394
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0394.pdf


    384. Automatic data reduction equipment for wind tunnels

    G. C. Rowley
    ARC/CP-399
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0399.pdf


    385. Calculated aerodynamic forces on a sweptback untapered wing oscillating in incompressible flow

    D. L. Woodcock
    ARC/CP-411
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0411.pdf


    386. Calculation of the shape of a thin slender wing for a given load distribution and planform

    J. H. B. Smith
    ARC/CP-385
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0385.pdf


    387. Complex variable applications to certain coupled systems

    D. P. Jenkins
    ARC/CP-393
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0393.pdf


    388. Critical flight conditions and loads resulting from inertia cross-coupling and aerodynamic stability deficiencies

    W. J. G. Pinsker
    ARC/CP-404
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0404.pdf


    389. Development and flight tests of an instrument flight director for helicopters

    P. Brotherhood
    ARC/CP-390
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0390.pdf


    390. Effects of some changes in body length and nose shape on the aerodynamic characteristics of wing-body combinations at supersonic speeds

    S. Tomlin and A. Stanbrook
    ARC/CP-413
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0413.pdf


    391. Experimental correlation between the endurance of a wing spar joint and the ratio between 0.1 percent proof and ultimate tensile strengths of the material

    W.A.P. Fisher
    ARC/CP-371
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0371.pdf


    392. High reynolds number tests on a 70 degrees L.E. sweepback delta wing and body (H.P. 100) in the compressed air tunnel

    R. W. F. Gould, and C. F. Cowdrey
    ARC/CP-387
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0387.pdf


    393. Low-speed wind-tunnel tests of the effects of various leading-edge modifications on the sectional characteristics of a thin wing (6 per cent thick, R.A.E. 101 section)

    S.F.J. Butler
    ARC/CP-410
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0410.pdf


    394. Measurements of the effect of surface cooling on boundary layer transition on a 15 degrees cone part 1 tests at M = 2 and 3 in an 8 in. x 9 in. wind tunnel at R.A.E./Bedford

    A. C. Browning, J. F. W. Crane and R. J. Monaghan
    ARC/CP-381
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0381.pdf


    395. Multi-channel slip rings for stress and temperature measurement

    R. Chaplin
    ARC/CP-389
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0389.pdf


    396. Notes on some simple strain gauge networks commonly used with wind tunnel balances

    J. R. Anderson
    ARC/CP-415
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0415.pdf


    397. Numerical aspects of unsteady lifting-surface theory at supersonic speeds

    H. C. Garner
    ARC/CP-398
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0398.pdf


    398. On the control of shock-induced boundary-layer separation with discrete air jets

    R. A. Wallis and C. M. Stuart
    ARC/CP-595
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0595.pdf


    399. One-dimensional treatment of weak disturbances of a shockwave

    Alan Powell
    ARC/CP-441
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0441.pdf


    400. Real gas effects on shock-tube performance at high shock strengths

    J. L. Stollery
    ARC/CP-403
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0403.pdf


    401. Records of Static Pressure Tests on Pressure Cabins

    P. B. Hovell and A. R. Butler
    ARC/CP-376
    1958

    Records are given of the strengths under static pressure of test specimens of twenty different types of pressurised fuselage.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0376.pdf


    402. Regularities in creep and hot-fatigue data part 1

    A. Graham and K. F. A. Walles
    ARC/CP-379
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0379.pdf


    403. Regularities in creep and hot-fatigue data part 2

    K. F. A. Walles and A. Graham
    ARC/CP-380
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0380.pdf


    404. Report of the definitions panel on definitions to be used in the description and analysis of drag

    Aeronautical Research Council
    ARC/CP-369
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0369.pdf


    405. Some contributions to jet-flap theory and to the theory of source-flow from aerofoils

    L. C. Woods
    ARC/CP-388
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0388.pdf


    406. Some details of the quintic profile for use in the polhausen-type of boundary-layer calculation

    N. Curle
    ARC/CP-391
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0391.pdf


    407. Some methods of evaluating imperfect gas effects in aerodynamic problems

    G. A. Bird
    ARC/CP-397
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0397.pdf


    408. Some proposals regarding the definitions of terms relating to various flow regimes of a gas

    C. H. E. Warren and A. D. Young
    ARC/CP-368
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0368.pdf


    409. Some results of an investigation into the use of air injection in a model of the diffuser for the A.R.A. supersonic tunnel

    E. C. Carter and K. F. Tucker
    ARC/CP-386
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0386.pdf


    410. Some tests in a slotted-wall tunnel with various slot-entry shapes

    A. Chinneck and N. A. North
    ARC/CP-377
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0377.pdf


    411. Static and dynamic response of a design of differential pressure yawmeter at supersonic speeds

    L. J. Beecham and S. J. Collins
    ARC/CP-414
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0414.pdf


    412. Static response of a hemispherical-headed yawmeter at high subsonic and transonic speeds

    P.G. Hutton
    ARC/CP-401
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0401.pdf


    413. Tables of aerodynamic flutter derivatives for thin wings and control surfaces in two dimensional supersonic flow

    I. T. Minhinnick and D. L. Woodcock
    ARC/CP-382
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0382.pdf


    414. Tests on a two-dimensional slotted-wall wind tunnel with lateral obstructions behind the slots

    A. Chinneck, C. J. Berry and P. J. Peggs
    ARC/CP-372
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0372.pdf


    415. The calibration at transonic speeds of a mark 9A pitot static head with and without flow through the static slots

    D. G. Mabey
    ARC/CP-384
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0384.pdf


    416. The effect on weather minima of approach speed, cockpit cut-off angle and type of approach coupler for a given landing success rate and level of safety

    E. S. Calvert and J. W. Sparke
    ARC/CP-378
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0378.pdf


    417. The geometry of wing surfaces generated by straight lines and with a high rate of thickness taper at the root

    D. Peckham
    ARC/CP-383
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0383.pdf


    418. The influence of a model on plenum chamber indication of mach number in a slotted wall wind tunnel

    L.C. Squire, and A. Stanbrook
    ARC/CP-395
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0395.pdf


    419. The longitudinal response of an aircraft with auto-pilot, including an incidence term in the height control equation

    M. R. Watts and D. E. Fry
    ARC/CP-396
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0396.pdf


    420. The theoretical performances of shock tubes designed to produce high shock speeds

    B. D. Henshall
    ARC/CP-407
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0407.pdf


    421. Theoretical analysis of the heating of a composite slab, with applications to the kinetic heating of an aircraft wing

    E. C. Capey and K. I. McKenzie
    ARC/CP-412
    1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0412.pdf


    422. A family of camber lines for subsonic applications a modified form of the N.A.C.A. family with uniform loading over the forward part and linear loading over the rear part

    H. B. Squire
    ARC/CP-437
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0437.pdf


    423. A note on the control of secondary flow by using cascades of twisted blades

    Moira E. Martin
    ARC/CP-425
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0425.pdf


    424. A one-dimensional theory of liquid-fuel rocket combustion

    D.B. Spalding
    ARC/CP-445
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0445.pdf


    425. A one-dimensional theory of liquid-fuel rocket combustion 2 the influence of chemical reaction

    J. Adler
    ARC/CP-446
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0446.pdf


    426. A progress report on the University of Southampton hypersonic gun tunnel

    K. N. C. Bray, L. Pennelgion and R. A. East
    ARC/CP-457
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0457.pdf


    427. A simple method of improving the supersonic velocity distribution in a transonic tunnel having slotted walls

    C. N. Hall
    ARC/CP-421
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0421.pdf


    428. A survey of buffeting loads

    Diana M. Seal
    ARC/CP-584
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0584.pdf


    429. An experiment to determine the position of an equivalent actuator disc replacing a blade row of a turbomachine

    J. H. Horlock and E. C. Deverson
    ARC/CP-426
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0426.pdf


    430. An improvement of the velocity distribution predicted by linear theory for wings with straight subsonic leading edges

    D. G. Randall
    ARC/CP-418
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0418.pdf


    431. Atmospheric turbulence encountered by bristol freighter aircraft in United Kingdom, West Africa and New Zealand

    J. R. Heath-Smith
    ARC/CP-429
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0429.pdf


    432. Atmospheric turbulence encountered by super constellation aircraft

    J. R. Heath-Smith
    ARC/CP-432
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0432.pdf


    433. Comparative strength tests of tension bolts with UNF and BSF threads revised version of technical note no. Structures 212

    R.F. Mousley, F. Clifton and D. le Brocq
    ARC/CP-416
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0416.pdf


    434. Design and operation of the N.G.T.E. thermal shock analogue

    C. G. Stanworth and D. S. C. Paine
    ARC/CP-557
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0557.pdf


    435. Effects of interaction between boundary layers and external stream and of incidence on boundary-layer drag at supersonic speeds

    A. D. Young and S. Kirkby
    ARC/CP-451
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0451.pdf


    436. Fatigue loadings in flight loads in the tailplane and fin of a jet provost

    Anne Burns
    ARC/CP-440
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0440.pdf


    437. Flight measurements of the drag of an aircraft fitted with a rear fuselage fairing designed to reduce the transonic drag

    D. R. Andrews, F. W. Dee and D. Waters
    ARC/CP-459
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0459.pdf


    438. Flight tests of a simple method of measuring pressure distributions on a wing

    W. G. A. Port and J. C. Morrall
    ARC/CP-422
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0422.pdf


    439. Flutter of an untapered wing allowing for thermal effects

    E. G. Broadbent
    ARC/CP-442
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0442.pdf


    440. Low speed tunnel measurements of the ground effect on a 1/5th scale model of the swift

    M.N. Wood and W.J.G. Trebble
    ARC/CP-458
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0458.pdf


    441. Measurements in flight of the longitudinal stability derivatives of a 60 degrees delta wing aircraft (Fairey Delta 2)

    D.R. Andrews
    ARC/CP-639
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0639.pdf


    442. Measurements of Velocity Fluctuations in the Working Section of the R.A.E. 4ft.x 3ft. Wind Tunnel with Flow Disturbances in the Second Diffuser

    J. A. Lawford
    ARC/CP-455
    October, 1958

    An attempt has been made to determine whether a large contraction ratio and wire gauze screens in the maximum section would prevent unsteadiness of flow in the return circuit frcm affecting the flow in the working section.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0455.pdf


    443. Microwave techniques applied to the investigation of ionised gases in shock tubes

    D. L. Schultz
    ARC/CP-436
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0436.pdf


    444. Model tests on an effuser induction scheme for operating a transonic wind tunnel

    D. A. Spence and A. S. Bennett
    ARC/CP-420
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0420.pdf


    445. Non-equilibrium theory of an ideal-dissociating gas through a conical nozzle

    N. C. Freeman
    ARC/CP-438
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0438.pdf


    446. On boundary-layer transition wires

    J. C. Gibbings
    ARC/CP-462
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0462.pdf


    447. Preliminary note on the effect of inertia cross-coupling on aircraft response in rolling manoeuvres

    W. J. G. Pinsker
    ARC/CP-435
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0435.pdf


    448. Reduction of lift-dependent drag with separated flow

    G. H. Lee
    ARC/CP-593
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0593.pdf


    449. Shock speed and running time measurements in the N.P.L. hypersonic shock tunnel

    B. D. Henshall
    ARC/CP-443
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0443.pdf


    450. Some experiments with static tubes at transonic speeds in a slotted-wall wind tunnel

    E. W. E. Rogers and I. M. Hall
    ARC/CP-430
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0430.pdf


    451. Some Notes on the Use of Resistance Thermometers for the Measurement of Heat Transfer Rates in Shock Tubes

    B. D. Henshall and D. L. Schultz
    ARC/CP-408
    29th May, 1958

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0408.pdf


    452. Some results on the crazing of perspex including the effect of humidity

    B. A. Blythe and W. W. Wright
    ARC/CP-454
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0454.pdf


    453. Some simple conical camber shapes to produce low lift-dependent drag on a slender delta wing

    G. G. Brebner
    ARC/CP-428
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0428.pdf


    454. Stall Cell Propagation in Two Mismatched Compressor Stages

    R C. Turner, T. J. Hargest and R. A Burrows
    ARC/CP-449
    January, 1958

    This Memorandum describes an investigation into the flow fluctuations occurring in two mismatched stages in the N.G.T.E. 106 low speed compressor. Its purpose is to contribute to a general understanding of surging and unsteady flow phenomena in full scale compressors when operating in a mismatched condition.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0449.pdf


    455. Statistical analysis of a particular target manoeuvre

    R.W. Bain et al
    ARC/CP-423
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0423.pdf


    456. The 'Newtonian' theory of hypersonic flow for any three-dimensional body

    N. C. Freeman
    ARC/CP-439
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0439.pdf


    457. The aerodynamic effects of aspect ratio on control surface flutter

    H. Hall and E. W. Chapple
    ARC/CP-434
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0434.pdf


    458. The distribution of gusts in the atmosphere an integration of U.K. and U.S. data

    N. I. Bullen
    ARC/CP-419
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0419.pdf


    459. The Effect of Axial Spacing on the Surge Characteristics of Two Mismatched Axial Compressor Stages

    R. C. Turner
    ARC/CP-431
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0431.pdf


    460. The flow upstream of finite span spoilers at supersonic speeds

    A. Stanbrook
    ARC/CP-427
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0427.pdf


    461. The influence of drag characteristics on the choice of landing approach speeds

    D. Lean, and R. Eaton
    ARC/CP-433
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0433.pdf


    462. The interaction between a weak normal shock wave and a turbulent boundary layer

    G. E. Gadd
    ARC/CP-424
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0424.pdf


    463. The internal damping due to structural joints and techniques for general damping measurement

    D. J. Mead
    ARC/CP-452
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0452.pdf


    464. The noise field from designed nozzles at different mach numbers

    J. G. M. Williams and D. C. Stevenson
    ARC/CP-448
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0448.pdf


    465. The velocity distribution in a turbulent boundary layer on a flat plate

    R. A. Dutton
    ARC/CP-453
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0453.pdf


    466. Theoretical investigation of the sound field produced downstream of a choked two-dimensional channel due to unsteady upstream entropy fluctuations

    J. P. Appleton and H. J. Davies
    ARC/CP-461
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0461.pdf


    467. Theory of the burning of mono-propellant droplets

    D. B. Spalding and V. K. Jain
    ARC/CP-447
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0447.pdf


    468. Transonic flow over two-dimensional round-nosed aerofoils

    D.G. Randall
    ARC/CP-456
    1959

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0456.pdf


    469. A comparison between the measured and predicted cooling performance of an internally spanwise ventilated turbine nozzle blade

    R. I. Hodge
    ARC/CP-494
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0494.pdf


    470. A correlation between rain erosion of perspex specimens in flight and on a ground rig

    T. J. Methven and B. Fairhead
    ARC/CP-496
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0496.pdf


    471. A flight investigation into the persistence of trailing vortices behind large aircraft

    T. H. Kerr and F. Dee
    ARC/CP-489
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0489.pdf


    472. A list of the journals and periodicals to which reference is made in incompressible aerodynamics and laminar boundary layers together with their abbreviations

    Aeronautical Research Council
    ARC/CP-444
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0444.pdf


    473. A measured power spectrum of the vertical component of atmospheric turbulence

    J. K. Zbrozek and D. M. Ridland
    ARC/CP-522
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0522.pdf


    474. A method of detecting the fully cooled state of a liquid oxygen pipeline

    N. Shufflebotham
    ARC/CP-573
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0573.pdf


    475. A one-dimensional theory of liquid-fuel rocket combustion 3 the effect of non-uniform droplet radii, injection velocities and physical properties

    J. Adler
    ARC/CP-469
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0469.pdf


    476. A photographic study of the impact between water drops and a surface moving at high speed

    D. C. Jenkins and J. D. Booker
    ARC/CP-501
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0501.pdf


    477. A preliminary note on a modified type of air jet for boundary-layer control

    R. A. Wallis
    ARC/CP-513
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0513.pdf


    478. A semi-empirical method for estimating the rotary rolling moment derivatives of swept and slender wings

    W. J. G. Pinsker
    ARC/CP-524
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0524.pdf


    479. A turbine nozzle cascade for cooling studies part 1 the measurement of mean nusselt numbers at the blade surface

    R. I. Hodge
    ARC/CP-492
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0492.pdf


    480. A turbine nozzle cascade for cooling studies part 2 comparison between measured and predicted mean nusselt numbers at the blade surface

    R. I. Hodge
    ARC/CP-493
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0493.pdf


    481. A wind tunnel investigation into the factors affecting the spanwise load distribution over the vertical tail surface of an aircraft having a wedge-type rear fuselage

    K. F. S. Chard, J. Deakin and A. R. Collar
    ARC/CP-491
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0491.pdf


    482. An approximate method for calculating the laminar boundary layer on an infinite swept wing with arbitrary velocity and suction distributions

    A. W. Lindfield and H. G. Pinsent
    ARC/CP-516
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0516.pdf


    483. An electrodynamic method of exciting servo-tabs for flight flutter testing

    W.H. Johnson
    ARC/CP-466
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0466.pdf


    484. An investigation at transonic speeds of the performance of various distributed rougness bands used to cause boundary-layer transition near the leading edge of a cropped delta half-wing

    E.W.E. Rogers et al
    ARC/CP-481
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0481.pdf


    485. An investigation into the effects of ground proximity on twin coaxial annular jets, using hotand cold air

    R. V. Barrett and J. C. Tipping
    ARC/CP-578
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0578.pdf


    486. An investigation of the flow over a half-wing model with 60.5 degrees leading edge sweepback, at a high subsonic and supersonic speeds

    F. O'Hara and J. B. Scott-Wilson
    ARC/CP-471
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0471.pdf


    487. Aspects of insect contamination in relation to laminar flow aircraft

    I. G. C. Lachmann
    ARC/CP-484
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0484.pdf


    488. Atmospheric turbulence encountered by viscount aircraft over Europe

    J.R. Heath-Smith
    ARC/CP-463
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0463.pdf


    489. Calculated leading-edge laminar separations from some RAE aerofoils

    N. Curle and S. W. Skan
    ARC/CP-504
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0504.pdf


    490. Calculation of cumulative effects from soaking at two or more temperatures

    Aeronautical Research Council
    ARC/CP-506
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0506.pdf


    491. Calculation of the recoil of a shock tube

    B. A. Woods
    ARC/CP-486
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0486.pdf


    492. Calculations of the lift slope and aerodynamic centre of cropped delta wings at supersonic speeds

    J. H. B. Smith, J. A. Beasley and A. Stevens
    ARC/CP-562
    July, 1960

    The linearised theory of supersonic flow is used to calculate the lift slope and the aerodynamic centre of cropped delta wings which have subsonic leading edges. The cropped tip must be short enough for each tip to lie entirely upstream of the disturbances produced by the other. The results are prezented graphically and in brief tables.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0562.pdf


    493. Comparison of theoretical and measured surface pressures at M = 1.2 on three bodies having different waistings

    W. R. Buckingham
    ARC/CP-520
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0520.pdf


    494. Crack propagation in sheet material - some conclusions deduced from a combination of theory and experiment

    D. Williams
    ARC/CP-467
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0467.pdf


    495. Effects of design speed and normal acceleration on aircraft structure weight

    M.E. Burt
    ARC/CP-490
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0490.pdf


    496. Fatigue loadings in flight - loads in the tailplane of a devon

    Anne Burns
    ARC/CP-472
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0472.pdf


    497. Fatigue loadings in flight loads in the nose undercarriage and wing of a valiant

    E. W. Wells
    ARC/CP-521
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0521.pdf


    498. Fatigue tests on notched extruded aluminium alloy (DTD 364B) having a theoretical stress concentration factor of 3.65

    W.A.P. Fisher
    ARC/CP-460
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0460.pdf


    499. Free-flight experiments on the measurement of free-stream static pressure at transonic speeds with particular reference to the Mk.9 pitot-static head

    C. Kell
    ARC/CP-475
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0475.pdf


    500. List of current papers published for the Aeronautical Research Council (numbers 401-450)

    Aeronautical Research Council
    ARC/CP-450
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0450.pdf


    501. Measurements of the effect of surface cooling on boundary layer transition on a 15 degrees cone part 2 tests at M = 3 and M = 4 in the 5 in. x 5 in. no. 5 wind tunnel at R.A.E. Farnborough

    J. G. Woodley
    ARC/CP-479
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0479.pdf


    502. Measurements of the velocity at the vortex centre on an A.R.1 delta wing by means of smoke observations

    A.P. Cox
    ARC/CP-511
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0511.pdf


    503. Methods of indicating a glide path by visual means

    J. W. Sparke
    ARC/CP-502
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0502.pdf


    504. Note on conditions for which data on the power spectra at atmospheric turbulence are required

    J. K. Zbrozek and F. Pasquill
    ARC/CP-474
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0474.pdf


    505. Power spectrum analysis of gust loads on the comet wing and tailplane

    D.T. Jones
    ARC/CP-465
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0465.pdf


    506. Preliminary Results of Low Speed Wind Tunnel Tests on a Gothic Wing of Aspect Ratio 1.0

    D. H. Peckham and S. A. Atkinson
    ARC/CP-508
    April, 1957

    This note gives preliminary results of low speed balance measurements and flow visualisation tests, on a wing of aspect ratio 1.0. The wing had a convex parabolic leading-edge shape in plan view, and an unswept trailing edge - such wings are now termed "Gothic". All edges were sharp, the centre section was 12% biconvex, and transverse sections were diamond-shaped. Results of tests on a strictly comparable delta wing are not yet available, but where possible the results are compared with tests on other wings of aspect ratio 1.0 with unswept trailing edges.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0508.pdf


    507. Pressure and boundary-layer measurements on a tapered swept wing in flight

    D. Hyde
    ARC/CP-560
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0560.pdf


    508. Pressure distributions at zero lift for delta wings with rhombic cross sections

    E. Eminton
    ARC/CP-525
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0525.pdf


    509. Programme fatigue tests on notched bars to a gust load spectrum

    W.A.P. Fisher
    ARC/CP-498
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0498.pdf


    510. Simulation of visual flight, with particular reference to the study of flight instruments

    J. M. Naish
    ARC/CP-488
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0488.pdf


    511. Some calculations by the Crocco-Lees and other methods of interactions between shock waves and laminar boundary layers, including effects of heat transfer and suction

    K. N. C. Bray, G. E. Gadd and M. Woodger
    ARC/CP-556
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0556.pdf


    512. Some fatigue tests on notched specimens with programme loading for a "ground-attack" aircraft

    W.A.P. Fisher
    ARC/CP-497
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0497.pdf


    513. Some instabilities arising from the interactions between shock waves and boundary layers

    N. C. Lambourne
    ARC/CP-473
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0473.pdf


    514. Some measurements in the vortex flow generated by a sharp leading edge having 65 degrees sweep

    N. C. Lambourne and D. W. Bryer
    ARC/CP-477
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0477.pdf


    515. Some notes on the possible application of thermoelectric devices to the generation of electric power

    P. J. Bateman
    ARC/CP-499
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0499.pdf


    516. Some Tests on an Avon-Canberra Installation to Measure Thrust in Flight

    R. Holl, R.G. Lea and Sqn.Ldr. J.E. Boden
    ARC/CP-518
    June, 1955

    Three aerodynamic methods of thrust measurement have been investigated:- (i) The "standard" single pitot method. (ii) The use of a jet ripe pitot pressure rake. (iii) The use of a pitot-static pressure rake at the plane of the final nozzle.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0518.pdf


    517. Some tests on cascades of compressor blades fitted with vortex generators

    R. Staniforth
    ARC/CP-487
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0487.pdf


    518. Stagnation-point heat-transfer rate measurements in the unexpanded flow of the N.P.L. hypersonic shock tunnel

    B. D. Henshall
    ARC/CP-468
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0468.pdf


    519. Static tests on a conical centrebody supersonic air intake with an auxiliary air inlet slot

    M. Cox
    ARC/CP-515
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0515.pdf


    520. Stress distribution in pressurized cabins an experimental study by means of xylonite models

    T. H. Richards
    ARC/CP-503
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0503.pdf


    521. Tests on a .03 scale model of the vickers M.T.1000 (C.132D) in the compressed air tunnel, N.P.L

    C. J. W. Miles and R. C. Fox
    ARC/CP-485
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0485.pdf


    522. The aerodynamic drag of near earth satellites

    G. E. Cook
    ARC/CP-523
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0523.pdf


    523. The centre section shape of swept tapered wings with a linear chordwise load distribution

    J.C. Cooke
    ARC/CP-470
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0470.pdf


    524. The cooling performance of two extruded-type air-cooled turbine nozzle blades

    R. I. Hodge
    ARC/CP-495
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0495.pdf


    525. The damping of structural vibrations

    G. G. Parfitt and D. Lambeth
    ARC/CP-596
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0596.pdf


    526. The effect of bend outlet conditions in the pressure losses in bent circular pipes

    Moira E. Martin and E. C. Deverson
    ARC/CP-505
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0505.pdf


    527. The effect of fuselage modifications on the zero-lift transonic drag of a fighter aircraft (hunter F. Mk.1) as measured by free-flight model tests

    G. H. Greenwood
    ARC/CP-482
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0482.pdf


    528. The longitudinal frequency response to elevator of an aircraft over the short period frequency range

    D. M. Ridland
    ARC/CP-476
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0476.pdf


    529. The rotating flap as a high-lift device

    L. F. Crabtree
    ARC/CP-480
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0480.pdf


    530. The shapes and lift-dependent drags of some sweptback wings designed for Mo = 1.2

    J.A. Bagley, and J.A. Beasley
    ARC/CP-512
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0512.pdf


    531. Thermal degradation of certain polymers under oxidative conditions

    D. B. V. Parker
    ARC/CP-464
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0464.pdf


    532. Turbulence encountered by ambassador aircraft over Europe

    J. R. Heath-Smith
    ARC/CP-574
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0574.pdf


    533. Visualization of secondary flow in the reservoirs of the slotted - wall working sections of the A.R.L. 12-inch and 30-inch water tunnels

    D. A. E. Leaver
    ARC/CP-483
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0483.pdf


    534. Wall interference at transonic speeds on a hemisphere-cylinder model

    E. W. E. Rogers, and I. M. Hall
    ARC/CP-510
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0510.pdf


    535. Wind tunnel flutter tests on an M-planform wing

    W.G. Molyneux
    ARC/CP-509
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0509.pdf


    536. Wind tunnel measurements of lift, drag and pitching moment of two highly swept (ALçE = 87 degrees and 81 degrees) delta wing-body combination models with small tip fins at M = 2.47

    P.J. Bateman
    ARC/CP-514
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0514.pdf


    537. Wind tunnel measurements of normal force and pitching moment on four cone-cylinder combinations at transonic and supersonic speeds

    E. Huntley
    ARC/CP-507
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0507.pdf


    538. Wind tunnel measurements of the lift-dependent drag of thin conically cambered slender delta wings at mach numbers 1.4 and 1.8

    M. S. Igglesden
    ARC/CP-519
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0519.pdf


    539. Wind tunnel tests on the flutter of a swept and unswept wing with ailerons

    H. Hall and J.A. Rein
    ARC/CP-478
    1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0478.pdf


    540. A crude theory of hovercraft performance at zero tilt

    S. B. Gates
    ARC/CP-608
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0608.pdf


    541. A force-displacement indicator for a drag balance

    R. E. Franklin
    ARC/CP-549
    July, 1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0549.pdf


    542. A method for designing body shape to produce prescribed pressure distributions on wing-body combinations at supersonic speeds

    J. G. Jones
    ARC/CP-540
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0540.pdf


    543. A note on the effects of heat transfer on the separation of a laminar boundary layer

    G. E. Gadd and J. L. Attridge
    ARC/CP-569
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0569.pdf


    544. A note on the use of steady expansions in shock tubes and shock tunnels

    D. L. Schultz
    ARC/CP-558
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0558.pdf


    545. A preliminary study of ionic recombination of argon in wind tunnel nozzles

    K. N. C. Bray and J. A. Wilson
    ARC/CP-559
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0559.pdf


    546. A wind tunnel investigation into the pressure distribution on a wing surface in a non-uniform supersonic flow

    M. C. P. firmin and W. J. Bartlett
    ARC/CP-551
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0551.pdf


    547. An experimental investigation of cavitation inception in the rotor blade tip region of an axial flow pump

    A. B. Mitchell
    ARC/CP-527
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0527.pdf


    548. An experimental study of the drag of rigid models representing two parachute designs at M = 1.40 and 2.19

    B. G. Roberts
    ARC/CP-565
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0565.pdf


    549. An Experimental Study of the Glancing Interaction between a Shock Wave and a Turbulent Boundary Layer

    A. Stanbrook
    ARC/CP-555
    July, 1960

    An experimental study has been made at Mach numbers from 1.6 to 2.0 of the interaction between the turbulent boundary layer on a side wall of a wind tunnel and the shock wave produced by a plate mounted on the wall. Under these conditions the shock wave/boundary layer interaction was three dimensional at least over the region investigated (up to 10 boundary layer thicknesses from the plate).

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0555.pdf


    550. Atmospheric turbulence encountered over the atlantic by stratocruiser aircraft

    Judy E. Aplin
    ARC/CP-533
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0533.pdf


    551. Automatic control of laboratory representation of kinetic heating

    J. Taylor
    ARC/CP-532
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0532.pdf


    552. Beating the heat barrier

    J. Taylor
    ARC/CP-545
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0545.pdf


    553. Boundary layer measurements at low speed on two wings of 45 degrees and 55 degrees sweep

    G. G. Brebner and L. A. Wyatt
    ARC/CP-554
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0554.pdf


    554. Comparative calculations of supersonic pitching derivatives over a range of frequency parameter

    H. C. Garner, W. E. A. Acum and Doris E. Lehrian
    ARC/CP-591
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0591.pdf


    555. Crack propagation properties of thin sheet - some recent results and their impact on design

    Williams, D
    ARC/CP-564
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0564.pdf


    556. Experimental study of the flow over a particular afterbody shape having a near-sonic ridge line

    D. Treadgold
    ARC/CP-546
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0546.pdf


    557. Exploratory tests on a thin delta wing in the flow field of a rectangular foreplane at mach number 1.8

    M. S. Igglesden and L. J. Beecham
    ARC/CP-530
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0530.pdf


    558. Exploratory tests on sting interference at a mach number of 6.8

    D. H. Peckham
    ARC/CP-566
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0566.pdf


    559. Flight measurements of the dutch roll characteristics of a 60 degree delta wing aircraft (fairey delta 2) at mach numbers from 0.4 to 1.5 with stability derivatives extracted by vector analysis

    R. Rose
    ARC/CP-653
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0653.pdf


    560. Flow field and pressure distribution measurements on blunt-nosed bodies at M = 6.8 parts 1 and 2

    W. K. Osborne and J. F. W. Crane
    ARC/CP-615
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0615.pdf


    561. Flow fluctuations and alternating blade stresses in a single-stage compressor a comparison with multi-stage tests

    R. Chaplin
    ARC/CP-537
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0537.pdf


    562. Free-flight measurements of control effectiveness on three wing planforms at transonic speeds

    J. B. W. Edwards
    ARC/CP-572
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0572.pdf


    563. Free-flight measurements of the zero-lift drag and base pressure on a wind tunnel interference model (M = 0.8-1.5)

    G. H. Greenwood
    ARC/CP-553
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0553.pdf


    564. Ground effect on a 55 degrees swept M-wing of aspect ratio 5.0

    L. A. Wyatt
    ARC/CP-541
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0541.pdf


    565. High reynolds number tests on an unswept 11% thick RAE 101 section aerofoil

    R. W. F. Gould, C. F. Cowdrey and P. G. G. O'Neill
    ARC/CP-531
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0531.pdf


    566. List of current papers published for the Aeronautical Research Council (numbers 451-500)

    Aeronautical Research Council
    ARC/CP-500
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0500.pdf


    567. Low-speed pressure-plotting tests on a flat-plate m-wing fitted with part-span nose-flaps

    L.A. Wyatt and G.P. Ilott
    ARC/CP-577
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0577.pdf


    568. Low-speed wind tunnel tests on a two-dimensional aerofoil with split flap near the ground

    J. A. Bagley
    ARC/CP-568
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0568.pdf


    569. Low-speed wind tunnel tests on the effects of taper on low aspect-ratio wings at zero incidence

    D. H. Peckham
    ARC/CP-571
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0571.pdf


    570. Low-speed wind-tunnel tests on sharp-edged gothic wings of aspect-ratio .75

    R. F. A. Keating
    ARC/CP-576
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0576.pdf


    571. Measurements of pitching oscillation derivatives at subsonic and transonic speeds for a cropped delta wing of aspect ratio 1.8 Interim Report

    C. J. W. Miles, J. B. Bratt, and K. B. Bridgman
    ARC/CP-534
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0534.pdf


    572. Measurements of the pitching moment derivatives for rigid wings of rectangular plan form oscillating about the mid-chord axis in supersonic flow

    C. Scruton et al
    ARC/CP-594
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0594.pdf


    573. Note on the time required for the achievement of steady flow past a slender body in a hypersonic shock tunnel

    D. W. Holder and D. L. Schultz
    ARC/CP-567
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0567.pdf


    574. On the representation of fan-wing characteristics in a form suitable for the analysis of transition motions, with results of tests of an aspect-ratio-1 wing with fan at 0.354 chord

    N. Gregory
    ARC/CP-552
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0552.pdf


    575. On the transient motion of a slender delta wing with leading edge separation

    G. J. Hancock
    ARC/CP-563
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0563.pdf


    576. Pressure Measurements at the Centre of a 40° Swept Back Wing with R.A.E. 101-10 Sections at Zero Incidence and Transonic Speeds

    J E. Rossiter
    ARC/CP-542
    June, 1959

    Pressure distributions have been measured on a 40° swept back wing with 10% thick R.A.E. 101 sections in combination with a rectangular section body.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0542.pdf


    577. Pressure measurements on three open nose air intakes at transonic and supersonic speeds, with an analysis of their drag characteristics

    J. C. Gibbings
    ARC/CP-544
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0544.pdf


    578. Progress report on an experiment on the effect of surface flexibility on the stability of laminar flow

    N. Gregory and Edna M. Love
    ARC/CP-602
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0602.pdf


    579. Scale models for thermo-aeroelastic research

    W. G. Molyneux
    ARC/CP-579
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0579.pdf


    580. Some characteristics of rectangular multi-shock and isentropic external compression intakes at a mach number of 2.9

    R. A. Dutton and E. L. Goldsmith
    ARC/CP-630
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0630.pdf


    581. Some Surge Investigations on a Low Speed Compressor

    R.C. Turner and R.A. Burrows
    ARC/CP-548

    This paper summarises some exploratory tests on a low speed low pressure ratio multi-stage axial compressor, in which mismatching was simulated by appropriate staggering of the stages, the last stage alone being unchanged. Overall and stage characteristics and surge flow coefficients were determined for two degrees of mismatching and for the fully matched condition. In addition, velocity and yaw traverses were made at the first and last stages, and flow fluctuation measurements were also made at selected positions.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0548.pdf


    582. Surface oil-flow patterns on wings of different leading-edge radius and sweepback

    H. C. Garner, and D. K. Cox
    ARC/CP-583
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0583.pdf


    583. Tests of an aerodynamic debris guard for a supersonic turbojet intake

    G. T. Golesworthy
    ARC/CP-561
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0561.pdf


    584. The acceleration of water drops by an airstream of constant relative velocity

    D. C. Jenkins
    ARC/CP-539
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0539.pdf


    585. The analysis of complex vibrations with spada

    S. L. Entres
    ARC/CP-570
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0570.pdf


    586. The calculated effect of the station of maximum cross-sectional area on the wave drag of delta wings

    J. H. B. Smith and W. Thomson
    ARC/CP-606
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0606.pdf


    587. The calculation of optimum incidences for aerofoils

    A. D. S. Carter
    ARC/CP-646
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0646.pdf


    588. The calculation of transient temperatures in turbine blades and tapered discs using biot's variational method

    P. W. H. Howe
    ARC/CP-617
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0617.pdf


    589. The design and testing of a low range acceleration transducer with predictable response characteristics

    I. McLaren
    ARC/CP-575
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0575.pdf


    590. The development of a static tube which is insensitive to incidence at supersonic speeds

    J. E. G. Townsend
    ARC/CP-543
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0543.pdf


    591. The effect of skin taper on the aeroelastic properties of wings

    J. A. Rein
    ARC/CP-642
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0642.pdf


    592. The estimation of transient temperature distributions and thermal stresses in turbine and compressor discs

    M. Cox
    ARC/CP-586
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0586.pdf


    593. The fatigue strength characteristics of a single spar wing

    W. J. Winkworth
    ARC/CP-535
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0535.pdf


    594. The low speed performance of low stagger compressor blading at three pitch/chord ratios

    R. C. Turner and R. A. Burrows
    ARC/CP-547
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0547.pdf


    595. The measurement of sub-critical damping on the R.A.E. flutter simulator

    J. Appleton and W. D. Hicks
    ARC/CP-529
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0529.pdf


    596. The performance of a cascade fitted with blown flaps

    R.A. Kruger, H. Marsh and J.H. Horlock
    ARC/CP-526
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0526.pdf


    597. The testing and development of a ground muffler for jet engine exhaust noise

    D. Middleton
    ARC/CP-610
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0610.pdf


    598. The use of woollen felt screens as air cleaners for supersonic wind tunnels

    J. F. W. Crane
    ARC/CP-538
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0538.pdf


    599. Trials of an experimental low airspeed indicator for helicopters

    Staff of Airborne and Helicopter Division, ARC
    ARC/CP-536
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0536.pdf


    600. Wind tunnel experiments on a model of a tandem rotor helicopter

    A. S. Halliday, and D. H. Cox
    ARC/CP-517
    1961

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0517.pdf


    601. A comparison of two methods for predicting the potential flow around arbitrary airfoils in cascade

    D. Pollard and J. Wordsworth
    ARC/CP-618
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0618.pdf


    602. A consideration of the similarity requirements for aerothermoelastic tests on reduced scale models

    W. G. Molyneux
    ARC/CP-611
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0611.pdf


    603. A note on the generalisation of elastic curves representing parachute shapes

    W. G. S. Lester
    ARC/CP-665
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0665.pdf


    604. An amplitude probability analyser for use in turbulence and noise measurements

    R. F. Johnson
    ARC/CP-580
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0580.pdf


    605. An empirical prediction method for non-linear normal force on thin wings at supersonic speeds

    J.R. Collingbourne
    ARC/CP-662
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0662.pdf


    606. An experimental investigation of the characteristics of an ogee wing from M = 0.4 to M = 1.8

    L.C. Squire and D.S. Capps
    ARC/CP-585
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0585.pdf


    607. An investigation of two methods of suppressing shock oscillation ahead of conical centre-body intakes

    C. F. Griggs
    ARC/CP-605
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0605.pdf


    608. An investigation of wing-aileron flutter using ground launched rocket models

    D. R. Gaukroger and J. K. Curran
    ARC/CP-627
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0627.pdf


    609. Comparative thrust measurements on a series of jet-flap configurations and circular nozzles

    M. N. Wood
    ARC/CP-616
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0616.pdf


    610. Diffraction of oblique shock wave

    R. S. Srivastava
    ARC/CP-612
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0612.pdf


    611. Exploratory wind-tunnel investigations on a bluff body containing a lifting fan

    W. J. G. Trebble and J. Williams
    ARC/CP-597
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0597.pdf


    612. Gusts at low altitude in North Africa

    N. I. Bullen
    ARC/CP-581
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0581.pdf


    613. Inflatable servo actuators

    A.R. Mettam
    ARC/CP-671
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0671.pdf


    614. Laminar mixing of a non-uniform stream with a fluid at rest

    J. F. Nash
    ARC/CP-613
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0613.pdf


    615. List of current papers published for the Aeronautical Research Council (numbers 351-400)

    Aeronautical Research Council
    ARC/CP-400
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0400.pdf


    616. List of current papers published for the Aeronautical Research Council (numbers 501-550)

    Aeronautical Research Council
    ARC/CP-550
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0550.pdf


    617. List of current papers published for the Aeronautical Research Council (numbers 551-600)

    Aeronautical Research Council
    ARC/CP-600
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0600.pdf


    618. Minimum energy ballistic trajectories over a non-rotating earth

    G. B. Longden
    ARC/CP-604
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0604.pdf


    619. Non-equilibrium flow of a polyatomic gas through a normal shock wave

    P. A. Blythe
    ARC/CP-645
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0645.pdf


    620. Observations of Stall Cells in a Single Stage Compressor

    J. Durham
    ARC/CP-589
    March, 1961

    A specially developed pressure-measuring instrument has been used to observe instantaneous values of the pressure, velocity and direction of the flow in a single stage, low hub-tip ratio, axial compressor. During stall propagation, the flow appeared to change from a point on the unstalled characteristic towards a point on the fully stalled characteristic and back again. The stall cells occurred only at the tips of the rotor blades. Despite these large fluctuations in the instantaneous flow, the time-average overall pressure rise characteristic was of the "progressive stall" type. The experiment demonstrated, therefore, a realistic model for the theoretical analysis of fully-developed stall cells.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0589.pdf


    621. Pressure measurements at supersonic speeds on three uncambered conical wings of unit aspect ratio

    J. W. Britton
    ARC/CP-641
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0641.pdf


    622. Pressure measurements on a cone-cylinder-flare configuration at M = 6.85 and incidences up to 30 degrees

    D. H. Peckham
    ARC/CP-657
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0657.pdf


    623. Problems associated with the use of a false wall as a reflection plane for half model tests in the de Havilland high speed wind tunnel

    D. R. Holder and H. C. Farley
    ARC/CP-587
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0587.pdf


    624. Proving tests of a wingtip parachute installation on a venom aircraft, with some measurements of directional stability and rudder power

    F. W. Dee
    ARC/CP-658
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0658.pdf


    625. Slender not-so-thin wing theory

    J. C. Cooke
    ARC/CP-659
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0659.pdf


    626. Some three-dimensional effects of rotating stall

    S. L. Dixon
    ARC/CP-609
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0609.pdf


    627. Subjective response to sonic bangs

    M. J. Clarke and J. F. Wilby
    ARC/CP-588
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0588.pdf


    628. Surface pressures and structural strains resulting from fluctuations in the turbulent boundary layer of a fairey delta 2 aircraft

    D. R. B. Webb, A. R. Keeler, G. R. Allen
    ARC/CP-638
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0638.pdf


    629. The 7 in. x 7 in. hypersonic wind tunnel at R.A.E. Farnborough parts 1, 2 and 3

    J.F.W. Crane and L.F. Crabtree
    ARC/CP-590
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0590.pdf


    630. The calculation of the velocity distribution due to thickness for swept wings with subsonic edges at supersonic speeds

    A. B. Haines, K. Rollins and J. Osborn
    ARC/CP-654
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0654.pdf


    631. The calibration of a 60 degrees cone to measure mach number, total pressure and flow angles at supersonic speeds

    D. R. Andrews and W. G. Sawyer
    ARC/CP-628
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0628.pdf


    632. The construction and testing of a large axial flow compressor

    R. Shaw and A. Lewkowicz
    ARC/CP-620
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0620.pdf


    633. The development of the boundary layer in supersonic shear flow

    Ruth H. Rogers
    ARC/CP-599
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0599.pdf


    634. The effect of tip bluntness on boundary-layer transition on a 15 degrees included angle cone at M = 3.12 and 3.81

    Ruth H. Rogers
    ARC/CP-598
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0598.pdf


    635. The equilibrium piston technique for gun tunnel operation

    R. A. East and L. Pennelegion
    ARC/CP-607
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0607.pdf


    636. The evaluation of some commercial and development pressure gauges in a laboratory type shock tube with a view to their suitability for use in shock tunnels

    D. R. Stevens
    ARC/CP-677
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0677.pdf


    637. The use of dust deposition as a means of flow visualisation

    E. T. Hignett
    ARC/CP-631
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0631.pdf


    638. Wind tunnel tests at Mach numbers between 0.6 and 1.4 of a 60 degrees swept wing having an aerofoil section designed for subcritical flow at a Mach number of 1.2 part 1 9 percent thick section with "triangular" pressure distribution

    E. F. Lawlor
    ARC/CP-582
    1962

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0582.pdf


    639. 8 feet x 6 feet transonic wind tunnel tests on a .04 scale model of the fairey delta 2 (ER.103)

    D. J. Kettle
    ARC/CP-656
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0656.pdf


    640. A digital computer programme for the calculation of annular or two-dimensional supersonic potential flow in a duct by the method of characteristics

    P. G. Street
    ARC/CP-649
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0649.pdf


    641. A note on the use of end plates to prevent three-dimensional flow at the ends of bluff cylinders

    C. F. Cowdrey
    ARC/CP-683
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0683.pdf


    642. A preliminary study of ionic recombination of argon in wind-tunnel nozzles part 2

    K. N. C. Bray and J. A. Wilson
    ARC/CP-634
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0634.pdf


    643. A simplified treatment of losses for one-dimensional mixing between hot and cold gas streams at constant pressure and low velocity

    B. S. Stratford and J. G. Williams
    ARC/CP-686
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0686.pdf


    644. A theoretical investigation of the effect of change in axial velocity on the potential flow through a cascade of aerofoils

    D. Pollard and J. H. Horlock
    ARC/CP-619
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0619.pdf


    645. A time-division analogue multiplier for correlation measurements and mixing at frequencies up to 100 kilocycles per second

    R. F. Johnson
    ARC/CP-685
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0685.pdf


    646. Aerodynamic and mechanical tests of a model of a variable mach number nozzle

    Z. M. Jawor
    ARC/CP-629
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0629.pdf


    647. Atomic recombination in nozzles methods of analysis for flows with complicated chemistry

    K. N. C. Bray and J. P. Appleton
    ARC/CP-636
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0636.pdf


    648. Boundary layer characteristics of caret wings

    D. Catherall
    ARC/CP-694
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0694.pdf


    649. Determination of ion density and temperature of a water-stabilised arc from observations of the line profiles of the hydrogen lines H beta and H gamma

    P. S. Pusey, K. C. Lapworth and A. F. Metherell
    ARC/CP-614
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0614.pdf


    650. Diffraction of a plane straight shock wave

    R. S. Srivastava
    ARC/CP-603
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0603.pdf


    651. Equilibrium real-gas performance charts for a hypersonic shock-tube wind-tunnel employing nitrogen

    L. Bernstein
    ARC/CP-633
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0633.pdf


    652. Estimation of Stability Derivatives (State of the Art)

    H. H. B. M. Thomas
    ARC/CP-664
    August, 1961

    The methods at present available for the estimation of the usual longitudinal and lateral stability derivatives of an airoraft are briefly discussed for each derivative in turn. This is preoeded by an introductory seotion dealing with trends in airoraft geometry and their implications regarding the stability derivatives. To illustrate this further the general discussion of methods is followed by a rather more detailed consideration of the estimation of these derivatives for a slender-wing type airoraft, mainly at low speeds, when incidenoe effects are shown to be important.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0664.pdf


    653. Free-flight measurements of the dynamic longitudinal-stability characteristics of a wind tunnel interference model (M = 0.92 to 1.35)

    G. H. Greenwood
    ARC/CP-648
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0648.pdf


    654. Low speed wind tunnel tests on a kite balloon model

    M. H. Simonds
    ARC/CP-643
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0643.pdf


    655. Measurements of the moments of inertia of the avro 707B aircraft

    D. H. Perry
    ARC/CP-647
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0647.pdf


    656. Notes on some experimental and theoretical results for the boundary layer development aft of the shock in a shock-tube

    L. Bernstein
    ARC/CP-625
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0625.pdf


    657. On axial load diffusion into a thin-walled reinforced cylindrical shell

    E.H. Mansfield
    ARC/CP-644
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0644.pdf


    658. On the effect of fan and thrust engine loading on the transition power requirements of a fan wing

    N. Gregory
    ARC/CP-690
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0690.pdf


    659. On the extrapolation and scatter of creep data

    K. F. A. Walles and A. Graham
    ARC/CP-680
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0680.pdf


    660. On theoretical plasticity and crack propagation

    E. H. Mansfield
    ARC/CP-688
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0688.pdf


    661. On Three-Dimensional Bodies of Delta Planform which can Support Plane Attached Shock Waves

    D. H. Peckham
    ARC/CP-640
    March, 1962

    This Note collects together in one report available theoretical work on bodies which can support attached plane shock waves, discusses some of the possible merits of such shapes, and includes some calculations illustrating their properties. Also, some preliminary results from wind tunnel tests are given, together with details of proposed future tests.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0640.pdf


    662. Pitching derivatives for a gothic wing oscillating about a mean incidence

    H. C. Garner and Doris E. Lehrian
    ARC/CP-695
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0695.pdf


    663. Power spectra of the vertical component of atmospheric turbulence obtained from concurrent measurements on an aircraft and at fixed points

    A. Burns
    ARC/CP-689
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0689.pdf


    664. Preliminary measurements in a shock tunnel of shock angle and undersurface pressure related to a nonweiler wing

    L. Pennelegion and R. F. Cash
    ARC/CP-684
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0684.pdf


    665. Pressure measurements on a cone-cylinder-flare configuration at small incidences for M = 6.8

    J. G. Woodley
    ARC/CP-632
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0632.pdf


    666. Propagation of fatigue cracks in wide unstiffened aluminium alloy sheets

    K.D. Raithby and Marie E. Bebb
    ARC/CP-655
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0655.pdf


    667. Qualitative solutions of the stability equation for a boundary layer in contact with various forms of flexible surface

    T. Nonweiler
    ARC/CP-622
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0622.pdf


    668. Room temperature instability and fraction in rotating discs and correlation with bi-axial tensile test data

    N. E. Waldren and D. E. Ward
    ARC/CP-660
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0660.pdf


    669. Tabulated solutions of the equilibrium gas properties behind the incident and reflected normal shock-wave in a shock-tube 1 nitrogen 2 oxygen

    L. Bernstein
    ARC/CP-626
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0626.pdf


    670. Tensile instability of hollow rotating discs of uniform thickness

    P. B. Mellor and M. J. Percy
    ARC/CP-692
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0692.pdf


    671. Tests to high subsonic speeds in the 10 ft x 7 ft tunnel, of several wing-mounted air-brakes on a half-model of a four-jet bomber vickers valiant

    M. J. Richards and D. J. Harper
    ARC/CP-621
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0621.pdf


    672. The 7 in. x 7 in. hypersonic wind tunnel at R.A.E. Farnborough part 4 measurements of diffuser performance, blockage, starting loads and humidity

    J. F. W. Crane and J. G. Woodley
    ARC/CP-663
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0663.pdf


    673. The boundary layer drag of bodies with swept trailing edges in supersonic flow

    J. C. Cooke
    ARC/CP-699
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0699.pdf


    674. The comparison of theory and experiment for oscillating wings

    W. E. A. Acum
    ARC/CP-681
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0681.pdf


    675. The effect of an initial boundary layer on the development of a turbulent free shear layer

    J. F. Nash
    ARC/CP-682
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0682.pdf


    676. The influence of a wide hub on the room temperature burst strength of model steam turbine rotors

    N. E. Waldren and D. E. Ward
    ARC/CP-661
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0661.pdf


    677. The mixing with ambient air of a cold airstream in a centrifugal field

    B. S. Stratford, Z. M. Jawor and G. T. Golesworthy
    ARC/CP-687
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0687.pdf


    678. The pressure calibration of the R.A.E. 6 inch diameter shock tube with a view to its use as the driver of a cold high-density hypersonic tunnel

    S. G. Cox, R. J. Pallant and J. M. Shaw
    ARC/CP-698
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0698.pdf


    679. The Static and Dynamic Response Properties of Incidence Vanes with Aerodynamic and Internal Viscous Damping

    W. J. G. Pinsker
    ARC/CP-652
    August, 1962

    The various contributions to the static position error of practical incidence vanes are briefly reviewed. The dynamic response of a windvane is shown to depend critically on the aerodynamic damping and viscous friction acting on the vane. It is also shown that the vane responds differently to incidences generated by gusts, aircraft plunging and by aircraft rotary motion. Frequency response formulae and graphs are given to illustrate some typical cases.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0652.pdf


    680. Theoretical comparison of the flow over a flat delta wing and a rectangular pyramid

    E. Eminton
    ARC/CP-637
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0637.pdf


    681. Three-dimensional turbulent boundary layers

    J. C. Cooke
    ARC/CP-635
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0635.pdf


    682. Tunnel tests on a double cascade to determine the interaction between the rotor and the nozzles of a supersonic turbine

    B. S. Stratford and G. E. Sansome
    ARC/CP-693
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0693.pdf


    683. Turbulent boundary layers on delta wings at zero lift

    J. C. Cooke
    ARC/CP-696
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0696.pdf


    684. Two-dimensional separated or cavitating flow past a flat plate normal to the stream

    G. E. Gadd
    ARC/CP-697
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0697.pdf


    685. Unsteady lift slope values obtained from flight measurements in gusts

    D. M. Ridland
    ARC/CP-651
    1963

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0651.pdf


    686. 8 ft x 6 ft tunnel tests on a model of the De Havilland "blue streak" at mach numbers of 0.80 to 1.25

    A.L. Courtney
    ARC/CP-735
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0735.pdf


    687. 8 ft x 8 ft tunnel tests on a model of the de havilland 'blue streak'

    G. F. Moss and D. Isaacs
    ARC/CP-734
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0734.pdf


    688. A collection of data on the lift-dependent drag of uncambered slender wings at supersonic speeds

    A.L. Courtney
    ARC/CP-757
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0757.pdf


    689. A correlation of the forebody drag of cylinders with plane and hemispherical noses at mach numbers from zero to 2.5

    A. Stanbrook
    ARC/CP-709
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0709.pdf


    690. A free-flight investigation of wing-body junction design for a transonic swept-wing aircraft

    G. K. Hunt
    ARC/CP-759
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0759.pdf


    691. A microsecond response pressure transducer for blast wave measurements

    D. Pierce
    ARC/CP-747
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0747.pdf


    692. A study on the running times in shock tubes

    J. A. D. Ackroyd
    ARC/CP-722
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0722.pdf


    693. A theoretical approach to air bag shock absorber design

    A.C. Browning
    ARC/CP-751
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0751.pdf


    694. A theoretical survey of the potentialities of insulation and internal cooling for alleviation of steady kinetic heating

    D. J. McCue
    ARC/CP-744
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0744.pdf


    695. Aeroelastic problems of high speed aircraft

    D. Moxon
    ARC/CP-668
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0668.pdf


    696. Annual variation of flight loads recorded on viscount aircraft by means of the fatigue load meter

    R. Hain Taylor
    ARC/CP-667
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0667.pdf


    697. Atmospheric turbulence encountered by comet 2 aircraft carrying cloud collision warning radar

    Judy E. Aplin
    ARC/CP-713
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0713.pdf


    698. Calculation of the turbulent boundary layer in the nozzle of an intermittent axisymmetric hypersonic wind tunnel

    N. B. Wood
    ARC/CP-721
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0721.pdf


    699. Calibration methods for the accurate assessment of the static and dynamic performance of some flight test instruments

    I. McLaren
    ARC/CP-760
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0760.pdf


    700. Discrepancies between theoretical and experimental values of temperature behind a shock wave

    J. Wilson
    ARC/CP-712
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0712.pdf


    701. Experimental evidence on the drag at zero lift on a series of slender delta wings at supersonic speeds, and the drag penalty due to distributed roughness

    M.C.P. Firmin
    ARC/CP-737
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0737.pdf


    702. Fatigue behaviour under service and ground test conditions a comparison based on the Dakota wing

    W. J. Winkworth
    ARC/CP-666
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0666.pdf


    703. Flight measurements at subsonic speeds of the aileron rolling power and lateral stability derivatives lv and yv on a 60 degree delta wing aircraft (Fairey Delta 2)

    F. W. Dee
    ARC/CP-739
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0739.pdf


    704. Flutter calculations on a body with aft wings

    E.G. Broadbent and E.V. Hartley
    ARC/CP-761
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0761.pdf


    705. Flutter tests and calculations on an all-moving model fin

    J. K. Curran
    ARC/CP-714
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0714.pdf


    706. Forces on tethered ballistic missiles due to motor cut-off - a theoretical treatment

    D. Moxon
    ARC/CP-674
    August, 1960

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0674.pdf


    707. Free-flight measurements of the drag and longitudinal stability of a transonic M-wing aircraft

    J. B. W. Edwards
    ARC/CP-773
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0773.pdf


    708. Free-flight measurements of the zero-lift drag of a slender ogee wing at transonic and supersonic speeds

    J. B. W. Edwards
    ARC/CP-670
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0670.pdf


    709. Free-flight model drag measurements on a transonic fighter (gloster javelin)

    G.H. Greenwood
    ARC/CP-678
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0678.pdf


    710. Limit analysis of circular frames

    E. O. Imegwu
    ARC/CP-705
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0705.pdf


    711. List of current papers (numbers 601-650)

    Aeronautical Research Council
    ARC/CP-650
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0650.pdf


    712. Low speed wind tunnel calibration of a new pitot-static head (MK.10) insensitive to incidence

    D. G. Mabey
    ARC/CP-762
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0762.pdf


    713. Low-speed wind-tunnel tests on a series of cambered ogee wings

    P. B. Earnshaw
    ARC/CP-775
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0775.pdf


    714. Measurement of lift and pitching moment on four ogee wings at supersonic speeds

    L. C. Squire
    ARC/CP-673
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0673.pdf


    715. Measurements at transonic speeds of the sideforce and yawing moment on various store arrangements mounted beneath a 45 degrees swept wing-fuselage model

    P. Marsden, A.B. Haines
    ARC/CP-955
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0955.pdf


    716. Measurements of "aquaplaning height" on a meteor aircraft, and photos of flow pattern under a model tyre

    W. E. Gray
    ARC/CP-717
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0717.pdf


    717. Measurements of skin-effection using surface-pitot tubes in free flight at supersonic speeds

    J. B. W. Edwards
    ARC/CP-711
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0711.pdf


    718. Measurements of the free stream turbulence in the R.A.E. bedford 13 ft x 9 ft wind tunnel

    D. H. Ferriss
    ARC/CP-719
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0719.pdf


    719. Measurements of transient pressures on a narrow-delta wing due to an upward gust

    G. K. Hunt, D. R. Roberts and D. Walker
    ARC/CP-624
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0624.pdf


    720. Measurements of zero-lift drag at supersonic speeds for a symmetrical slender-wing model with different roughness bands

    E. C. Carter
    ARC/CP-741
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0741.pdf


    721. Notes on Ducted Fan Design

    R. C. Turner
    ARC/CP-895
    August, 1964

    In general, conventional compressor stages are designed by the cascade method, while high stagger low solidity ducted fans are designed on modified isolated aerofoil theory. The purpose of these notes is to provide a basis for disussion on the relative merits of the two methods and on the desirabi1ity of extending one method to cover the whole range of blading likely to be required in compressors and fans. Attention has been mainly oonfined to low speed two-dimensional considerations. It is suggested that the cascade approach could provide a basis for the formulation of a unified design method. A project of this nature mould necessitate a programme of testing and performance analysis of typical fans; high stagger cascade tests might also provide supporting data, although there could be doubts as to their sigmficance.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0895.pdf


    722. On forward ejection for thermal insulation in hypersonic flight

    M. G. Hall
    ARC/CP-752
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0752.pdf


    723. On the numerical calculation of theodorsen's transformation

    B. Thwaites
    ARC/CP-691
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0691.pdf


    724. On the theory of vibrational relaxation in gases

    E. Wild
    ARC/CP-725
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0725.pdf


    725. On the variation of profile drag coefficient below the critical mach number

    J. F. Nash, T. H. Moulden and J. Osborne
    ARC/CP-758
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0758.pdf


    726. Power spectra of low level atmospheric turbulence measured from an aircraft

    A. Burns
    ARC/CP-733
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0733.pdf


    727. Prandtl-Meyer flow in a relaxing gas

    P. A. Blythe
    ARC/CP-724
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0724.pdf


    728. Pressure, heat transfer and temperature measurements in the two-dimensional nozzle of a reflected-shock tunnel

    J. L. Stollery and J. E. G. Townsend
    ARC/CP-726
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0726.pdf


    729. Roughness criteria and drag penalties for bands of distributed roughness on two slender wings at supersonic speeds

    D. G. Mabey
    ARC/CP-738
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0738.pdf


    730. Side force on a wing body combination due to trailing vortices

    J.R. Barnes
    ARC/CP-669
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0669.pdf


    731. Some computer programmes for the calculation of chemical equilibrium composition, with application to combustion and propulsion systems

    Diana Raynor and J. B. J. Thorpe
    ARC/CP-769
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0769.pdf


    732. Some examples of the use of a conical shadowgraph technique

    D. Pierce and D. Treadgold
    ARC/CP-763
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0763.pdf


    733. Some notes on turbulent boundary layers with fluid injection at high supersonic speeds

    L. C. Squire
    ARC/CP-740
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0740.pdf


    734. Some simple calculations relating to the generation of an R.F. plasma

    E. G. Broadbent
    ARC/CP-746
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0746.pdf


    735. Some tests with trapped vortices in supersonic flow

    B. S. Stratford and M. C. Neale
    ARC/CP-716
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0716.pdf


    736. Static tests of ground effect on planforms fitted with a centrally-located round lifting jet

    L. A. Wyatt
    ARC/CP-749
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0749.pdf


    737. Supersonic wind tunnel measurements of the loads and internal pressure distributions on ducts at incidence

    P. H. Cook
    ARC/CP-768
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0768.pdf


    738. Tables of the function xnKn(x)/2n-1(n-1). for use as cumulative frequency distributions

    N. I. Bullen and Elizabeth Busby
    ARC/CP-765
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0765.pdf


    739. Temperature measurements on a plasma jet

    A. Wells and R. H. Kennett
    ARC/CP-756
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0756.pdf


    740. Tests on a hunter F.2 of two strain gauge methods for measuring tailplane loads in flight, with some loads measured in level flight, pitch-ups and transonic dives

    O.P. Nicholas
    ARC/CP-754
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0754.pdf


    741. The addition of peripheral vision to the artificial horizon

    K. J. Holden
    ARC/CP-731
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0731.pdf


    742. The drag of infinite swept wings with an addendum

    J. C. Cooke
    ARC/CP-1040
    June 1964

    The drag of an infinite swept wing is found in terms of the drag of a related unswept wing having the same relative position of transition. Results in incompressible flow are expressed in terms of a 'sweep factor'. Detailed calculations are made for wings of RAE 101 and 104 sections and the factor appears to have a reasonably universal character not very dependent on shape or Reynolds number if transition takes place early, but strongly dependent on thickness. Results are given as a series of curves and an empirical formula is given for the sweep factor in terms of thickness-chord ratio, angle of sweep and point of transition. A few results are given for compressible flow over an RAE 101 section at sweep angles of 0° and 45°; these show the effect of sweep in delaying the compressibility drag rise.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1040.pdf


    743. The effects of high pressure on the flow in the reflected shock tunnel

    L. Davies et al
    ARC/CP-730
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0730.pdf


    744. The estimation of oscillatory wing and control derivatives

    W. E. A. Acum and H. C. Garner
    ARC/CP-623
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0623.pdf


    745. The influence of gas streams and magnetic fields on electric discharges part 1 arcs at atmospheric pressure in annular gaps

    V. W. Adams
    ARC/CP-743
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0743.pdf


    746. The measured response of an aircraft to the vertical velocity component of atmospheric turbulence

    D. M. Ridland
    ARC/CP-708
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0708.pdf


    747. The pressure distribution at zero-lift on some slender delta wings at supersonic speeds

    M. C. P. Firmin
    ARC/CP-774
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0774.pdf


    748. Use of a wind tunnel to determine the performance of slender wings suitable for a supersonic transport aircraft

    J. Y. G. Evans
    ARC/CP-742
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0742.pdf


    749. Wind tunnel force and moment investigation at M = 4.3 into the application of various devices for the control of a cone-cylinder-flare configuration

    B. E. Pecover
    ARC/CP-745
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0745.pdf


    750. Wind tunnel measurements of normal force and pitching moment at a mach number of 2.00 on a 1:30 scale model of blue streak

    E. Huntley
    ARC/CP-732
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0732.pdf


    751. Wind tunnel tests at M = 2.0 on interference effects between intake flows in a four-engine nacelle

    M. D. Dobson
    ARC/CP-753
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0753.pdf


    752. Wind tunnel tests at supersonic speeds on a model of the fairey delta 2

    M. D. Dobson
    ARC/CP-672
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0672.pdf


    753. Wind-tunnel experiments on a simple lifting-jet body with and without wings

    W. J. G. Trebble
    ARC/CP-718
    1964

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0718.pdf


    754. A comparison of rivet shear strengths obtained from two-rivet specimens and from multi-rivet specimens at room temperature and 150 degrees C

    D. F. Wright, P. Judson, and P. W. Horrocks
    ARC/CP-794
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0794.pdf


    755. A comparison of the measured and predicted flutter characteristics of a wing-aileron-tab model

    H. Hall
    ARC/CP-715
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0715.pdf


    756. A digital recording system for structural research

    D. Purslow
    ARC/CP-825
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0825.pdf


    757. A note on the estimation of the effect of wind tunnel walls on the forces on slowly oscillating slender wings

    W. E. A. Acum
    ARC/CP-707
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0707.pdf


    758. A parameter theory for the compressible flow through variable-area turbo-machines

    Gordon S. Beavers
    ARC/CP-755
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0755.pdf


    759. A parametric study of take-off and landing distances for high-lift aircraft

    W. A. Mair and B. J. Edwards
    ARC/CP-823
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0823.pdf


    760. A problem of wing-body interference

    D. G. Randall
    ARC/CP-704
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0704.pdf


    761. A semi-empirical prediction method for pressures on the windward surface of circular cones at incidence at high supersonic and hypersonic speeds (M is greater than or equal to 3)

    J. R. Collingbourne, L. F. Crabtree, and W. J. Bartlett
    ARC/CP-792
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0792.pdf


    762. A simple method for real gas flow calculations

    J. L. Wilson and J. D. Regan
    ARC/CP-772
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0772.pdf


    763. A simple method of calculating the flow produced in an annular electric arc heater

    J. M. Shaw
    ARC/CP-779
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0779.pdf


    764. A unified theory of friction, heat transfer and mass transfer in the turbulent boundary layer and wall jet

    D. B. Spalding
    ARC/CP-829
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0829.pdf


    765. Aircraft vortex wakes and their effects on aircraft

    R. Rose and F. W. Dee
    ARC/CP-795
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0795.pdf


    766. Alleviation of thermal stresses in aircraft structures

    E. C. Capey
    ARC/CP-819
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0819.pdf


    767. An experimental check on the theoretical relationship between the spectral density and the probability distribution of crossings for a stationary random process with Gaussian distribution, using data obtained in measurements of aircraft response to turbul

    J. Burnham
    ARC/CP-834
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0834.pdf


    768. An experimental investigation into the determination of lift from wake traverses at supersonic speeds

    J. Wooller, M.C.P. Firmin
    ARC/CP-801
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0801.pdf


    769. Analysis of flight loads recorded on comet 4B aircraft by means of the fatigue load meter

    R. Hain Taylor
    ARC/CP-820
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0820.pdf


    770. Annular cascade experimental investigations of conical actuator disc theory and of non-uniform flow through plane walled diverging or converging ducts

    R. I. Lewis
    ARC/CP-766
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0766.pdf


    771. Atmospheric turbulence encountered by Hermes aircraft on routes to Africa and the Far East

    Judy E. Aplin
    ARC/CP-785
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0785.pdf


    772. Bow-shock establishment and stagnation-point pressure measurements for a blunt-nosed body at supersonic speeds

    L. Davies
    ARC/CP-776
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0776.pdf


    773. Calculated Lift Distributions in Incompressible Flow on Some Sweptback Wings

    J.A Bagley and G.M. Joyce
    ARC/CP-675
    August, 1962

    In the course of a larger survey of some aerodynamic characteristics of a family of sweptback wings, the ion-speed lift distributions were calculated. The 35 planforms considered cover a range of leading-edge sweep angles from 55° to 70°, and aspect ratios from 2 to 3.9. The results are given here, together with a comparison with other calculations and with experimental results on one particular wing.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0675.pdf


    774. Calculations of the thermodynamic properties of nitrogen at high pressures

    J. L. Wilson and J. D. Regan
    ARC/CP-771
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0771.pdf


    775. Effect of flow curvature due to the fuselage on the flapping motion of a helicopter rotor

    M. A. P. Willmer
    ARC/CP-782
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0782.pdf


    776. Effect on the static strength of aluminium alloy test specimens of the attachment of thermocouples by a welding technique

    D. F. Wright and G. F. Acheson
    ARC/CP-790
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0790.pdf


    777. Effects of varied loading paths on fatigue endurances part 1 some load fatigue properties of nimonic 90 at elevated temperatures

    G. P. Tilly
    ARC/CP-786
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0786.pdf


    778. Effects of varied loading paths on fatigue endurances part 2 some load fatigue properties of H46 at room temperature

    G. P. Tilly
    ARC/CP-787
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0787.pdf


    779. Effects of varied loading paths on fatigue endurances part 3 some stress fatigue properties of H46 at elevated temperatures

    G. P. Tilly
    ARC/CP-788
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0788.pdf


    780. Excitation temperature measurements of gases in an arc-heated wind tunnel at 1.3 x 10-2 atmosphere using relative intensities of spectral lines

    B. D. Adcock and W. E. G. Plumtree
    ARC/CP-701
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0701.pdf


    781. Experimental investigation of the breakdown of a vortex in a tube

    D. L. I. Kirkpatrick
    ARC/CP-821
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0821.pdf


    782. Experiments at hypersonic speeds on circular cones at incidence

    D.H. Peckham
    ARC/CP-702
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0702.pdf


    783. Flight and tunnel tests to develop a thermal detector for determining the boundary layer state

    Ann Cronin and O.P. Nicholas
    ARC/CP-781
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0781.pdf


    784. Free-flight measurements of pressure and heat transfer in regions of separated and reattached flow at mach numbers up to 4

    J. Picken
    ARC/CP-706
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0706.pdf


    785. Free-flight model measurements of the dynamic stability of a supersonic strike aircraft (TSR2)

    G. K. Hunt, A. Jean Ross
    ARC/CP-918
    November 1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0918.pdf


    786. High pressure real gas drivers and tailoring in shock tunnels

    L. Davies
    ARC/CP-770
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0770.pdf


    787. Influence of chemical contouring on the fatigue and sustained load properties of high tensile steel sheet

    Westland Aircraft Limited, Saunders-Roe Division
    ARC/CP-812
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0812.pdf


    788. List of current papers (numbers 651-700)

    Aeronautical Research Council
    ARC/CP-700
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0700.pdf


    789. List of current papers (numbers 701-750)

    Aeronautical Research Council
    ARC/CP-750
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0750.pdf


    790. List of current papers (numbers 751-800)

    Aeronautical Research Council
    ARC/CP-800
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0800.pdf


    791. Low altitude gust measurements over three routes in the U.K

    E. W. Wells
    ARC/CP-676
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0676.pdf


    792. Mach number distributions along the slotted walls of the N.P.L. 20 in. x 8 in. high-speed wind tunnel

    H. H. Pearcey, and J. D. Regan
    ARC/CP-784
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0784.pdf


    793. Measurement of aerodynamic heat transfer in intermittent wind-tunnels

    A. Naysmith
    ARC/CP-780
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0780.pdf


    794. Measurement of air temperature on an aircraft travelling at high subsonic and supersonic speeds

    A. A. Woodfield and P. J. Haynes
    ARC/CP-809
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0809.pdf


    795. Measurements of dynamic stability from three simplified free-flight models of a supersonic research aircraft (Bristol T.188) over the mach number range 1.2 - 2.6

    K. J. Turner
    ARC/CP-816
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0816.pdf


    796. Measurements of oscillatory derivatives at mach numbers up to 2.6 on a model of a supersonic transport design study (Bristol type 198)

    J. S. Thompson, R. A. Fail
    ARC/CP-815
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0815.pdf


    797. Measurements of pressure fluctuations on the surface of a delta wing

    V. Krishnamoorthy
    ARC/CP-767
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0767.pdf


    798. Measurements of skin-friction in an annulus by the floating element technique

    J. K. White and R. E. Franklin
    ARC/CP-814
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0814.pdf


    799. Measurements of vortex-breakdown position at low speed on a series of sharp-edged symmetrical models

    P. B. Earnshaw
    ARC/CP-828
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0828.pdf


    800. Methods and charts for estimating skin friction drag in wind tunnel tests with zero heat transfer

    K. G. Smith
    ARC/CP-824
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0824.pdf


    801. On the calculation of cascade flows

    W. S. Hall and B. Thwaites
    ARC/CP-806
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0806.pdf


    802. Potential flow through cascades a comparison between exact and approximate solutions

    J. P. Gostelow
    ARC/CP-807
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0807.pdf


    803. Potential flow through cascades extensions to an exact theory

    J. P. Gostelow
    ARC/CP-808
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0808.pdf


    804. Pressure distribution measurements on a series of slender delta body shapes at mach numbers of 6.85 and 8.60

    D. H. Peckham
    ARC/CP-791
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0791.pdf


    805. Preston tube measurements in turbulent boundary layers and fully developed pipe flow

    D. H. Ferriss
    ARC/CP-831
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0831.pdf


    806. Proposals for an integrated wind tunnel-flight dynamics simulator system

    L.J. Beecham, W.L. Walters and D.W. Partridge
    ARC/CP-789
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0789.pdf


    807. Radio propagation through rocket exhaust jets part 1 electromagnetic wave propagation in an ionised medium

    H. Williams
    ARC/CP-764
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0764.pdf


    808. Review of general operating experience with a jet-lift VTOL research aircraft (short S.C.1)

    D. Lean and H. W. Chinn
    ARC/CP-832
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0832.pdf


    809. Simulation of ground controlled approaches with reference to certain accidents

    K. J. Holden
    ARC/CP-748
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0748.pdf


    810. Slender-body theory calculations of the effect on lift and moment of mounting the wing off the fuselage centre-line

    R. S. Bartlett
    ARC/CP-830
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0830.pdf


    811. Supersonic wind tunnel tests on a 1/12th scale model of the bristol type 188 research aircraft part 1 M = 1.4 to 2.0 part 2 M = 2.0 to 2.7

    C. R. Taylor and T. A. Cook
    ARC/CP-818
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0818.pdf


    812. Tests with a variable ramp intake having combined external/internal compression, and a design mach number of 2.2

    M. C. Neale and P. S. Lamb
    ARC/CP-805
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0805.pdf


    813. The calculation of aircraft motion in design rolling manoeuvres

    D. J. Eckford
    ARC/CP-799
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0799.pdf


    814. The calculation of pressure distribution in steady supersonic flow, with arbitrary downwash distribution

    Laura Klanfer
    ARC/CP-703
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0703.pdf


    815. The chance of a rough flight

    N. I. Bullen
    ARC/CP-836
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0836.pdf


    816. The change of pitot pressure across oblique shock waves in a perfect gas

    W. J. Graham and B. M. Davis
    ARC/CP-783
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0783.pdf


    817. The chemical contouring of 3 percent chromium-molybdenum-vanadium and 5 percent chromium-molybdenum-vanadium high strength steel sheet

    Bristol Aerojet Ltd
    ARC/CP-811
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0811.pdf


    818. The design and development of an air-bearing for the measurement of damping in yaw on a jet-blowing model

    A. P. Cox
    ARC/CP-796
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0796.pdf


    819. The mixing between hot and cold airstreams in a centrifugal field

    B. S. Stratford, Z. M. Jawor and Maureen M. Smith
    ARC/CP-793
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0793.pdf


    820. The movement of high-current arcs in transverse external and self-magnetic fields in air at atmospheric pressure

    H.C. Spink, and A.E. Guile
    ARC/CP-777
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0777.pdf


    821. The static pressure distribution around a circular jet exhausting normally from a plane wall into an airstream

    L. J. S. Bradbury and M. N. Wood
    ARC/CP-822
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0822.pdf


    822. The steady flow of a viscous fluid past a circular cylinder

    S. C. R. Dennis and M. Shimshoni
    ARC/CP-797
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0797.pdf


    823. The time required for high speed airstreams to disintegrate water drops

    D. C. Jenkins and J. D. Booker
    ARC/CP-827
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0827.pdf


    824. The unsteady motion of slender wings with leading-edge vortices

    B. D. Dore
    ARC/CP-810
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0810.pdf


    825. Theoretical investigation of some basic assumptions of Schlichting's singularity method of cascade analysis

    R. I. Lewis and G. A. Pennington
    ARC/CP-813
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0813.pdf


    826. Theoretical stability derivatives for a symmetrically tapered wing at low supersonic speeds

    Doris E. Lehrian and Gillian Smart
    ARC/CP-736
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0736.pdf


    827. Wind tunnel measurements at mach numbers up to 2.80 of the effects of gulling on the longitudinal and lateral stability and drag of a cambered, slender ogee wing

    T. A. Cook
    ARC/CP-803
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0803.pdf


    828. Wind tunnel measurements of the far-field pressures due to some lifting, slender delta wings

    T. A. Cook
    ARC/CP-802
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0802.pdf


    829. Wind tunnel measurements of the unsteady pressures in and behind a bomb bay (Canberra)

    J. E. Rossiter and A. G. Kurn
    ARC/CP-728
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0728.pdf


    830. Wind tunnel tests at mach numbers up to 1.8 on a model with .03 scale wings and nacelles of a twin-engined supersonic aircraft (Bristol 188)

    E.P. Sutton, P.G. Hutton and L.C. Squire
    ARC/CP-798
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0798.pdf


    831. Wind tunnel tests at mach numbers up to 2.80 to determine the effects of changing spanwise volume distribution on a slender, cambered ogee wing

    T. A. Cook
    ARC/CP-804
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0804.pdf


    832. Wind tunnel tests between M = 0.4 and 2.0 on a cambered wing of slender ogee planform

    M. D. Dobson and R. King-Underwood
    ARC/CP-778
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0778.pdf


    833. Wind tunnel tests on a 1/12th scale model of the bristol type 188 research aircraft with rectangular, wedge intakes at mach numbers from 2.0 to 2.7

    T. A. Cook
    ARC/CP-817
    1965

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0817.pdf


    834. A battery-operated four-channel tape recorder for use in acoustic measurements in flight

    F.L. Hunt, B. Fairhead
    ARC/CP-1010
    Ocober 1966

    This report describes a self-contained battery-operated four-channel tape recorder which has been designed particularly for the direct recording of audio frequency signals in a research aircraft where installation space was strictly limited and where no operating power was available from the aircraft electrical system.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1010.pdf


    835. A developed theory of spoilers on aerofoils

    C. S. Barnes
    ARC/CP-887
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0887.pdf


    836. A method for correcting measurements of the heat transfer factor through the skin of a wind tunnel model

    B. A. M. Piggott
    ARC/CP-860
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0860.pdf


    837. A new method of measuring the impedance of the human respiratory system at moderate frequencies

    K. R. Maslen, G. F. Rowlands
    ARC/CP-1031
    September 1966

    The stability of aircrew breathing equipment depends not only on the stability of the oxygen regulator, but also on the impedance of the system it feeds, which includes the user's respiratory system. A method of measuring the human respiratory impedance, in the range 5-90 c/s, by comparing oscillating pressures at two points in an external reference system, is described; and results are given for nose and mouth, heavy and light, breathing. The effect of altitude, and of increased external resistance to breathing are briefly discussed. The importance of correct representation of man's impedance in dynamic testing of oxygen equipment is illustrated by reference to the characteristics of a present-day simulator and system, and an improved type of simulator is suggested.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1031.pdf


    838. A note on skin-friction laws for the incompressible turbulent boundary layer

    J. F. Nash
    ARC/CP-862
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0862.pdf


    839. A note on the deck landing velocities of helicopters

    M.A.P. Willmer
    ARC/CP-854
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0854.pdf


    840. A note on the turbulent uniform-property hydrodynamic boundary layer on a smooth impermeable wall comparisons of theory with experiment

    M. P. Escudier and D. B. Spalding
    ARC/CP-875
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0875.pdf


    841. A procedure for the determination of cascade characteristics

    J. A. P. Stoddart and D. Gardner
    ARC/CP-870
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0870.pdf


    842. A review of information on the frequency of gusts at low altitude

    N. I. Bullen
    ARC/CP-873
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0873.pdf


    843. A survey of aircraft handling criteria

    C. Leyman and E. R. Nuttall
    ARC/CP-833
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0833.pdf


    844. A survey of unsteady hypersonic flow problems

    B. M. Wood
    ARC/CP-901
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0901.pdf


    845. A technique for studying high-velocity drawing in polymers

    G. W. H. Stevens and F. C. Bluett
    ARC/CP-1061
    August 1966

    The principle of elastic relaxation is considered as a technique for drawing polymers at high velocities. The theory is worked out and some tests are described in which skeins of low density polyethelene filaments have been drawn using some heat-set terylene webbing as the elastic. These tests, in which polythene was drawn at a velocity of about 50 feet per second at a temperature of about l8°C, demonstrated that the technique is feasible. Comparison with the theory suggests that the force to draw at this speed is about twice that measured at very slow rates of drawing.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1061.pdf


    846. A technique for the wind tunnel simulation of store release at high speeds

    L. J. Beecham
    ARC/CP-856
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0856.pdf


    847. A velocity defect relationship for the outer part of equilibrium and near-equilibrium turbulent boundary layers

    J. McQuaid
    ARC/CP-885
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0885.pdf


    848. Aerodynamic characteristics at M = 4.3 of monoplane, triform and cruciform slender delta wing bodies with all-moving tail control surfaces

    D. Treadgold, D. Pierce
    ARC/CP-1014
    October 1966

    Supersonic wind tunnel tests were made over an incidence range from -4 to +30 degrees for a range of roll angles on a scrims of conical slender delta wing and body combinations with a short afterbody on which a rectangular tail control surface is mounted. An examination is made of the characteristics of the wing and body combination and the approximate contributions of the individual Wing panels are deduced. The effectiveness of the tail control surfaces as stabilisers and as controls is examined for three different sizes of gap between the control and the wing trailing edge. The non linear behaviour of the oontrols tested is attributed at low incidences to the viscous losses due to the wing wake, and at high incidence to the influenoe of the expansion field from the wing trailing edge.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1014.pdf


    849. Aerodynamic study force and moment measurements on three delta wings of aspect ratios 0.83, 1.03 and 1.24 in combination with bodies of fineness ratio 13 at a mach number of 4

    D.R. Andrews
    ARC/CP-888
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0888.pdf


    850. An experimental investigation of the flow through inclined circular tubes at a mach number of 4.0

    P. L. Roe
    ARC/CP-884
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0884.pdf


    851. An experimental investigation of the influence of base bleed on the base drag of various propelling nozzle configurations

    J. B. Roberts and G. T. Golesworthy
    ARC/CP-892
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0892.pdf


    852. Analysis of hinge moment data for rectangular and near rectangular trailing edge controls at supersonic and transonic speeds

    D. Isaacs
    ARC/CP-874
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0874.pdf


    853. Approximate formulae for the lift and drag of wedge aerofoil sections at high supersonic speeds

    L. C. Squire
    ARC/CP-864
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0864.pdf


    854. Boundary layer separation in a centrebody nozzle with parallel shroud

    V. Herbert and R. J. Herd
    ARC/CP-853
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0853.pdf


    855. Bulk compressibility effects in the R.A.R.D.E. no. 3 hypersonic gun tunnel

    W. A. Clayden
    ARC/CP-882
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0882.pdf


    856. Calculations of the structure of unsteady rarefaction waves in oxygen/argon mixtures, allowing for vibrational relaxation

    J. P. Appleton
    ARC/CP-720
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0720.pdf


    857. Characteristics of aft mounted all-moving rectangular control surfaces on a slender cruciform model at Mach numbers from 0.6 to 2.8

    K. G. Winter, Susan M. Mills
    ARC/CP-1011
    Ocober 1966

    The wings are of delta planform, with aspect ratio of exposed pairs of panels 0.31, and total span of 2.5 times the diameter of the body, which is of fineness ratio 19. The rectangular controls, of span equal to that of the wings, and the chord 0.5 times the body diameter, are mounted with a half chord gap to the wing trailing edge. Loads are measured on one control in addition to overall loads. The tests cover an incidence range up to 22 degrees for 0 and 45 degrees roll and a complete roll range for incidences of 6, 12 and 20 degrees with elevator angles of 0, 10, 20 and 30 degrees. A brief survey of the flow in the region of the tail at M = 2.8 at an incidence of 20 degrees is included. The results show that there are large variations with roll angle in both stabiliser effectiveness in pitch and elevator effectiveness. Aileron effectiveness is fairly constant. The rolling moment variation with roll angle on the complete model changes from being stable when one pair of wings is horizontal for all incidences at subsonic speeds and for low incidence at supersonic speeds, to being unstable for high incidence at supersonic speed. It is suggested that this effect may arise mainly from the interaction of the body vortices and of the vortices from the near horizontal wings with the wing on the leeside of the body.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1011.pdf


    858. Comparison of helicopter and aeroplane vertical accelerations in turbulence

    D. A. Webber
    ARC/CP-878
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0878.pdf


    859. Comparison of seven wing buffet boundaries measured in wind tunnels and in flight

    D. G. Mabey
    ARC/CP-840
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0840.pdf


    860. Diffraction of blast wave for the oblique case

    R. S. Srivastava
    ARC/CP-1008
    December, 1966

    The problem of diffraction of an oblique shook wave has been considered in this paper. The investigations are devoted to the cases when the relative outflow behind the reflected shock before diffraction is subsonic and sonic. The distribution of pressure has been obtained for finite and infinite shock strengths for both these cases.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1008.pdf


    861. Free-flight tests of vortex generator configurations at transonic speeds

    J.B.W. Edwards
    ARC/CP-729
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0729.pdf


    862. Further measurements of transient pressures on a narrow-delta wing due to a vertical gust

    D. R. Roberts, G. K. Hunt
    ARC/CP-1012
    April 1966

    Transient pressures have been measured on the upper surface of a narrow delta wing when it passed through newly sharp-edged upward and downward gusts. Some characteristics of the transient behaviour of the vortex flow on the wing have been identified and discussed. It is shown that a gust-induced loss of lift on this kind of wing develops more rapidly than a gust-induced gain of lift, and thus produces the greater change of loading.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1012.pdf


    863. Further tests on a three-stage turbine of low reaction to examine the effects of reduced rotor pitch and improved sealing

    I. H. Johnston and D. C. Dransfield
    ARC/CP-861
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0861.pdf


    864. Further tests with a variable ramp intake having a design mach number of 2.2

    M. C. Neale and P. S. Lamb
    ARC/CP-826
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0826.pdf


    865. Gun tunnel measurements of lift, drag and pitching moment on a 20 degrees cone, a flat delta and a caret delta wing at a mach number of 8.3

    T. Opatowski
    ARC/CP-908
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0908.pdf


    866. Handling qualities of aircraft with marginal longitudinal stability

    T.B. Saunders
    ARC/CP-837
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0837.pdf


    867. Interim report on low-speed flight tests of a slender-wing research aircraft (Handley-page H.P.115)

    P. L. Bisgood and C. O. O'Leary
    ARC/CP-838
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0838.pdf


    868. Laminar boundary layers with uniform fluid properties. similar solutions to the velocity equation involving mass transfer

    H. L. Evans
    ARC/CP-857
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0857.pdf


    869. Low-speed tunnel tests of an aspect-ratio 9 jet-flap model, with ground simulation by moving-belt rig

    S. F. J. Butler, B. A. Moy, and G. D. Hutchins
    ARC/CP-849
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0849.pdf


    870. Low-speed wind-tunnel measurements of the lift, drag and pitching moment on three symmetrical ogee-wing models and on a symmetrical slender wing-body model

    D. A. Kirby
    ARC/CP-846
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0846.pdf


    871. Low-speed wind-tunnel tests on a delta-wing aircraft model (S.R. 177), with blowing over the trailing-edge flaps and ailerons

    S. F. J. Butler and M. B. Guyett
    ARC/CP-710
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0710.pdf


    872. Measurement of turbulence in the liverpool university turbomachinery wind tunnels and compressor

    R. Shaw, A. K. Lewkowicz and J. P. Gostelow
    ARC/CP-847
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0847.pdf


    873. Measurements of the rolling response of a fighter aeroplane (hunter MK.6) to turbulent air and a comparison with theory

    J. Burnham
    ARC/CP-898
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0898.pdf


    874. Mercury programmes for lifting surface theory calculations on wings oscillating in supersonic flow

    G. S. Harris
    ARC/CP-851
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0851.pdf


    875. Normal accelerations measured in the cockpit and at the C.G. of a jet transport aeroplane during flight through rough air

    J. Burnham
    ARC/CP-867
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0867.pdf


    876. Notes on the automatic control of a blowdown wind tunnel

    P. G. Pugh and L. C. Ward
    ARC/CP-1029
    July 1966

    This report briefly describes salient results obtained during commissioning Or the stagnation pressure control system of the N.P.L. 15 in x 10 in (38.1 cm x 25.4 cm) blowdown wind tunnel. The very different problems of low and high Mach number operation are examined, and the representation of the various flow processes in a manner suitable for an analogue computer is discussed.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1029.pdf


    877. On the interaction of the transmitted shock with the boundary layer in a shock tube using argon as test gas

    L. Davies and K. Bridgman
    ARC/CP-879
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0879.pdf


    878. Plasma flow in an electromagnetic shock tube and in a compression shock tube

    J. L. Wilson, D. Schofield and J. D. Regan
    ARC/CP-886
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0886.pdf


    879. Simple theoretical and experimental studies of the flow through a three-shock system in a corner

    E. Eminton
    ARC/CP-727
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0727.pdf


    880. Some studies of pressure distributions on the windward surfaces of conical bodies at high supersonic speeds

    A. Akers
    ARC/CP-723
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0723.pdf


    881. Supersonic laminar boundary layers on cones

    J. C. Cooke
    ARC/CP-1063
    November 1966

    The boundary layer flow over a cone inclined at a small angle to a supersonic stream, and over a type of caret (Maikapar, Nonweiler) surface, as generalised by Townend, is calculated by an implicit finite difference method. Prandtl number is arbitrary but viscosity must follow the Chapman-Rubesin law. Any (conical) distribution of wall temperature or heat flux can be covered; the effects of suction or blowing can only be included if the normal velocity along a ray varies inversely as distance from the apex. Some sample calculations are made. The method begins to break down as separation is approached, but it is not difficult to find the separation line by extrapolation.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1063.pdf


    882. The calculation of the shape of an electric arc discharge rotating in an annular gap under the influence of a non-uniform longitudinal applied magnetic field

    J. M. Shaw
    ARC/CP-858
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0858.pdf


    883. The economic effects of meteorological forecasting standards for supersonic civil transports

    A. L. Courtney
    ARC/CP-1028
    September 1966

    As an aid to discussions on the future provision of meteorological forecasting services for civil transport operations, an approximate assessment is made of the effects of changes in the accuracy with which en-route and take-off winds and temperatures can be forecast. The results are given in terms of the annual value calculated over the world total of long-range civil operations, first for a current subsonic fleet equivalent to about 350 Boeing 707's and then for a possible supersonic fleet equivalent to about 4.00 Concords, such as might be in operation in 1980-1985. It is found that in current long-range subsonic operations the accurate forecasting of en-route winds is the most important item. In future supersonic operations, however, the most important item is likely to be the accurate fore-casting of en-route temperature, wind being of comparatively minor importanoe. Accuracy in forecasting the airfield temperature for take-off is also likely to be important for supersonic transports.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1028.pdf


    884. The effect of external flow on an internal-expansion propelling nozzle incorporating ventilation by ambient air

    M. V. Herbert et al
    ARC/CP-897
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0897.pdf


    885. The flapping behaviour of a helicopter rotor at high tip-speed ratios

    E. Wilde, A. R. S. Bramwell, R. Summerscales
    ARC/CP-877
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0877.pdf


    886. The interaction of the reflected shock with the boundary layer in a shock tube and its influence on the duration of hot flow in the reflected-shock tunnel part 1

    L. Davies
    ARC/CP-880
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0880.pdf


    887. The interpretation of strain measurements for flight load determination

    P. B. Hovell, D. A. Webber, T. A. Roberts
    ARC/CP-839
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0839.pdf


    888. The lateral oscillation of slender aircraft

    A. J. Ross
    ARC/CP-845
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0845.pdf


    889. The lift and drag characteristics of caret wings at Mach numbers between 5 and 10

    J.R. Collingbourne, D.H. Peckham
    ARC/CP-930
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0930.pdf


    890. The magnetic deflection of short arcs rotating between annular electrodes above and below atmospheric pressure

    E. D. Blix and A. E. Guile
    ARC/CP-843
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0843.pdf


    891. The motion of helicopter blades at low rotor speeds in high winds

    M. A. P. Willmer
    ARC/CP-852
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0852.pdf


    892. The performance of a centrebody propelling nozzle with a parallel shroud in external flow part 1

    R. J. Herd and G. T. Golesworthy
    ARC/CP-841
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0841.pdf


    893. The performance of a centrebody propelling nozzle with a parallel shroud in external flow part 2

    M. V. Herbert, G. T. Golesworthy and R. J. Herd
    ARC/CP-894
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0894.pdf


    894. The performance of a conical convergent-divergent nozzle with area ratio 2.9 in external flow

    G. T. Golesworthy and M. V. Herbert
    ARC/CP-891
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0891.pdf


    895. The performance of conical convergent-divergent nozzles of area ratios 2.44 and 2.14 in external flow

    G. T. Golesworthy, J. B. Roberts and C. Overy
    ARC/CP-893
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0893.pdf


    896. The pilot's safety problem in category 2 operations and the potential contribution of head-up display. Initial investigation of head-up display at B.L.E.U

    J. C. Morrall
    ARC/CP-1001
    June 1966

    This paper aims to fulfil two main functions; firstly, it highlights what is believed to be the main safety problem in current bad weather landing and secondly, it presents results of initial flight trials with a head-up display which show that this aid has great potential value for Category II operations. The safety problem is shown to lie in the limitations of the pilot in controlling the aircraft in pitch, using visual guidance. The head-up display is recommended as a solution to this problem as it can provide an efficient means of combining instrument and visual information. In addition, further improvements could be achieved by optimisation of cockpit procedures, whether or not a head-up display is adopted.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1001.pdf


    897. The problem of panel flutter with reference to the blue streak and black knight vehicles

    G. Z. Harris
    ARC/CP-848
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0848.pdf


    898. The response times of typical transducer-tube configurations for the measurement of pressures in high-speed wind tunnels

    M. J. Larcombe and J. W. Peto
    ARC/CP-913
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0913.pdf


    899. The role of compressive stress in the load and strain fatigue behaviour of H.46 at room temperature

    G. P. Tilly
    ARC/CP-844
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0844.pdf


    900. The use of air injection to prevent separation of the turbulent boundary layer in supersonic flow

    D. J. Peake
    ARC/CP-890
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0890.pdf


    901. Theoretical stability derivatives for a symmetrically tapered wing of aspect ratio 3 at supersonic speeds

    Doris E. Lehrian
    ARC/CP-855
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0855.pdf


    902. Turbulent boundary layer theory and its application to blade profile design

    D. J. L. Smith
    ARC/CP-868
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0868.pdf


    903. Turbulent-boundary-layer behaviour and the auxiliary equation

    John F. Nash
    ARC/CP-835
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0835.pdf


    904. Two-dimensional normal fences on a flat plate

    C. S. Barnes
    ARC/CP-863
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0863.pdf


    905. Vertical accelerations due to structural vibrations of a slender aircraft flying in continuous turbulence

    J. K. Zbrozek
    ARC/CP-842
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0842.pdf


    906. Wind tunnel experiments on a lifting jet in a bluff body with and without wings

    W. J. G. Trebble
    ARC/CP-859
    1966

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0859.pdf


    907. "Zero rate of climb speed" as a low speed limitation for the stall-free aircraft

    W. J. G. Pinsker
    ARC/CP-931
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0931.pdf


    908. A comparison of some methods for predicting creep strain and rupture under cyclic loading

    J. M. Clarke
    ARC/CP-1020
    April 1967

    There are many good reasons for attempting to predict creep behaviour under conditions of varying stress and temperature from data derived from tests perfomed at constant stress and temperature. This Report starts by describing the most straightforward hypotheses at present used for this purpose. Computed results for cyclic variations have shown that (i) the "strain hardening" and "life fraction" hypotheses predict very similar rupture times, (ii) the times to a given creep strain do not depend on the frequency of the cycles or the sequence of loading within the cycles providing there are several (10 or more) cycles involved, (iii) when a substantial proportion (more than about two-thirds) of the creep life shows a "tertiary" behaviour the "time hardening" hypothesis predicts the shortest rupture times for the same cyclic loading. A method is demonstrated for evaluating effective mean stresses or temperatures for any cyclic conditions according to either strain or time hardening hypotheses.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1020.pdf


    909. A convenient representation of creep strain data for problems involving time-varying stresses and temperatures

    J. M. Clarke
    ARC/CP-945
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0945.pdf


    910. A flight simulation study of difficulties in piloting large jet transport aircraft through severe atmospheric disturbances

    D. H. Perry, J. Burnham
    ARC/CP-906
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0906.pdf


    911. A model for the aquaplaning of tyres on wet runways

    J. C. Cooke
    ARC/CP-1078
    September 1967

    An attempt is made to estimate pressure distribution, tyre deflection and lift on a fully aquaplaning smooth tyre assuming an idealised non-viscous flow in front of the tyre followed by Stokes flow under the tyre. The problem is reduced to solving two coupled partial differential equations, namely Rayleigh's lubrication equation for the water and the membrane equation for the tyre. It appears that viscosity is not important except for the no-slip condition it implies. The conclusion is reached that it will be essential to solve a three-dimensional free stream surface problem in order to make further progress.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1078.pdf


    912. A note on the design and construction of a low-pressure calibrator and a comparison with shock-tube and static calibration methods

    R. J. Pallant
    ARC/CP-947
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0947.pdf


    913. A preliminary experimental investigation of shock-wave development on aerofoils

    T. H. Moulden, I. J. Cox, V. A. Stringfellow
    ARC/CP-964
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0964.pdf


    914. A preliminary flight simulation study of jet-borne V.T.O.L. aircraft handling qualities

    D. H. Perry, H. W. Chinn
    ARC/CP-902
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0902.pdf


    915. A review of counting accelerometer data on aircraft gust loads

    N. I. Bullen
    ARC/CP-933
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0933.pdf


    916. A semi-empirical theory for the growth and bursting of laminar separation bubbles

    H. P. Horton
    ARC/CP-1073
    June 1967

    A simple pressure gradient criterion for the determination of the conditions under which re-attachment of a turbulent clear layer can occur is proposed. Application of this criterion to the laminar separation bubble problem, together with a simple bubble model and an approximate method of calculation of the momentum thickness growth over the bubble, leads to a method of prediction of the bubble growth. It is found that for a given imposed pressure distribution there exists a Reynolds number at separation below which re-attachment is impossible; this is associated with the so-called 'bursting' phenomenon. The predicted bursting parmeters are in good agreement with experimental observations; in particular, the value of Crabtree's pressure rise parameter is found to be weakly dependent upon the boundary-layer Reynolds number at separation, varying between the limits 0.27 to 0.36 over the range of practical significance. It is concluded that bursting occurs as a failure of the re-attachment process, as suggested by Woodward.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1073.pdf


    917. A short static probe with good incidence characteristics at supersonic speed

    I. S. Donaldson and D. J. Richardson
    ARC/CP-1099
    October 1967

    Tests carried out on a short static probe at supersonic speeds between Mach numbers of 1.1 and 2.5 are described. The probe consists of a 50° included angle cone-cylinder having sensing holes 0.98 calibres aft of the cone-cylinder junction. The tests show that at zero incidence the probe measures a pressure (approximately independent of Mach number) of 0.793 times the local static pressure. They also show that, at up to l8° incidence in any pitch plane, the pressure measured is 0.763 ±0.33 times the local static pressure. For a limited Mach number range near a Mach number of 1.6, this accuracy can be maintained to incidences over 30°. Of particular interest is the fact that relatively small internal differences between externally identical probes appear to have a significant effect on the incidence characteristics and in some respects can improve the performance.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1099.pdf


    918. A short time response stagnation temperature probe

    R. A. East and J. H. Perry
    ARC/CP-909
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0909.pdf


    919. A simple flexible supersonic wind tunnel nozzle for the rapid and accurate variation of flow mach number

    D. Pierce
    ARC/CP-865
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0865.pdf


    920. A study on the running times in reflected shock tunnels

    J. A. D. Ackroyd
    ARC/CP-883
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0883.pdf


    921. A survey of the mechanics of uniaxial creep deformation of metals

    J.W.L. Warren
    ARC/CP-919
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0919.pdf


    922. A theoretical investigation of the effect of aspect ratio on axial flow compressor performance

    J. H. Horlock and G. J. Fahmi
    ARC/CP-943
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0943.pdf


    923. A turbulent skin-friction law for use at subsonic and transonic speeds

    J. F. Nash and A. G. J. Macdonald
    ARC/CP-948
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0948.pdf


    924. A use of arbitrary modes in control-surface flutter investigations

    T. Niblett
    ARC/CP-928
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0928.pdf


    925. Aircraft loading actions problems - proceedings of a symposium held at Farnborough on 28 October 1966

    A. S. Taylor and D.J. Eckford
    ARC/CP-1003
    July 1967

    The symposium was held at the Farnborough Technioal College on 28 October 1966 and was attended by representatives of the Aeronautical Research Council, Universities and Colleges, the Aviation Industry, the Air Transport Operators, the Air Registration Board, and Government bodies. An Editorial Foreword, which sketches the background to the symposium, is followed by a Resume of the Proceedings. The papers presented are then reproduced in full together with accounts of the ensuing discussions.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1003.pdf


    926. An analogue computer for on-line correction of wind tunnel force and moment data

    B. E. Pecover
    ARC/CP-946
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0946.pdf


    927. An analysis of some major factors involved in normal take-off performance

    D. H. Perry
    ARC/CP-1034
    December 1967

    An analytical study has been made of the effect of such parameters as wing loading, aspect ratio, thrust-weight ratio, and number of engines, on the takeoff performance of fixed wing aircraft. Expressions are derived for the take-off lift coefficients which give the shortest take-off distance, the highest takeoff wing loading, and climb conditions just meeting the airworthiness requirements. Examples of the analysis applied to two designs of current interest are given.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1034.pdf


    928. An EMA program for the analysis of plane stress problems

    Jane Buller-Sinfield
    ARC/CP-1037
    October 1967

    A computer program in Extended Mercury Autocode (EMA) is described for the finite element analysis of plane stress problems in regions of arbitrary geometry, using constant strain triangular elements.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1037.pdf


    929. An experiment in turbine blade profile design

    I. H. Johnston and Diane Smart
    ARC/CP-941
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0941.pdf


    930. An experimental investigation of the two-dimensional wall jet

    James H. Whitelaw
    ARC/CP-942
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0942.pdf


    931. An inflated mobile lifting system for an 8 ton load

    I. S. H. Brown, F. T. Kiernan
    ARC/CP-1092
    August 1967

    A system comprising an inflatable load-lifting canopy of oval planform with buoyancy tube and separate trailer for inflation and towing over water has been proved feasible for loads of up to 8 tons over smooth ground and calm water. Limits of performance in more severe conditions have not been determined. For future applications and in particular for loads of various sizes and load distribution a circular planfom canopy should be considered, together with alternative methods of slinging, inflation and propulsion. When used over porous surfaces and uneven ground, a blower with increased airflow would be of advantage to maintain air pressure and reduce friction and abrasion of the base of the structure.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1092.pdf


    932. An investigation into a technique for measuring jet interference effects using free-flight models

    G. H. Greenwood
    ARC/CP-969
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0969.pdf


    933. An investigation of stress redistribution caused by creep in a thick-walled circular cylinder subjected to axial and thermal loading

    J. M. Clarke
    ARC/CP-1024
    June 1967

    A thick-walled tube was subjected to an axial load and a radial temperature distribution which caused thermal stresses. The creep strains and the eventual rupture times were observed and compared with conventional creep tests and theoretical analysis. Theory suggested and experiments confirmed that stress redistribution caused the overall strain behaviour to approach that for the mean axial stress and the mean radial temperature. Description of the experimental technique and apparatus includes a novel snd simple optical extensometer. Appendices contain a complete analytic treatment of the triaxial stress problem in a long thick tube in the presence of an arbitrary distribution of non-elastic strains, and a treatment of some conditions under which stress-redistribution calculations can lead to a "steady state" or "fully redistributed" stress pattern. A less rigorous theoretical treatment which ignores radial constraints is shown to lead to an under-estimate of the thermal stresses and of the time required for stress redistribution to occur.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1024.pdf


    934. Approximate solutions of the three-dimensional laminar boundary layer momentum integral equations

    P.D. Smith and A.D. Young
    ARC/CP-1064
    September 1967

    Six methods for the approximate solution of the three-dimensional laminar boundary layer momentum integral equations are presented and oompared with three known exact solutions. These methods all involve the Pohlhausen technique of specifying velocity profiles in terms of one or two unknowns and substituting these expressions for the profiles into the two momentum integral equations to render them determinate.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1064.pdf


    935. Atmospheric turbulence and aircraft height-keeping accuracy

    B. A. M. Piggott
    ARC/CP-1009
    August 1967

    As a contribution to the study of vertical separation standards for use in air traffic control, an examination is made of the possiblllty of applying the spectral methods already used in gust load evaluations to the problem of determining the height-keeping errors caused by atmospheric turbulence. Although it is found that the data available on the low frequency components of atmospheric turbulence and on the nature of the control applied by the pilot, whether human or automatic, are not sufficient to allow an accurate estimation of these errors, it is concluded that they do not make a significant contribution to the total errors experienced. It is noted, however, that certain atmospheric phenomena lie outside the scope of the theory used here.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1009.pdf


    936. Balance measurements (excluding drag) on a delta wing aircraft at transonic speeds

    M. M. Shaw
    ARC/CP-904
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0904.pdf


    937. Calculation of compressible turbulent boundary layer on a flat plate

    S. V. Patankar
    ARC/CP-1027
    August 1967

    Calculations are presented of the compressible turbulent boundary layer on a flat plate. They have been made by a new, general, accurate and economical procedure. The physical inputs chiefly comprise: (1) a form of the mixing-length hypothesis, and (ii) the assumption of a uniform effective Prandtl number. The predictions are compared with available experimental data and empirical correlations; the agreement is satisfactory. It is pointed out that the same method may be expected to give good predictions even in more complex situations.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1027.pdf


    938. Camber effects on the non-linear lift of slender wings with sharp leading edges

    L. C. Squire
    ARC/CP-924
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0924.pdf


    939. Characteristics of high-speed wind tunnels in the United Kingdom relevant to aeroelastic-model tests

    C. A. K. Irwin
    ARC/CP-876
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0876.pdf


    940. Civil aircraft airworthiness data recording programme study of severe turbulence encountered by civil aircraft

    G. E. King
    ARC/CP-974
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0974.pdf


    941. Computer programmes to calculate the response of flexible aircraft to gusts and control movements

    C. G. B. Mitchell
    ARC/CP-957
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0957.pdf


    942. Crack propagation in fatigue. Some experiments with DTD 5070A aluminium alloy sheet

    D. P. Rooke et al
    ARC/CP-896
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0896.pdf


    943. Crack propagation tests on 2024-T3 unstiffened aluminium alloy panels of various length-width ratios

    T. J. Carter
    ARC/CP-952
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0952.pdf


    944. Determination of stagnation temperatures in the R.A.R.D.E. hypersonic gun tunnel from streak camera measurements of flow velocity

    J. E. Bowman
    ARC/CP-929
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0929.pdf


    945. Estimation of surface pressures from observed shock-wave envelopes surrounding conical bodies at M = 4.0

    M. J. Larcombe
    ARC/CP-1085
    August 1967

    An optical method utilising a standard schlieren system is used to locate the position of the shock wave surrounding a conical body at a free stream Mach number of 4.0. An analysis of the conditions at the shock wave enable the surface pressure distribution to be calculated. Good agreement with experimental pressure distributions is obtained except in regions dominated by viscous effects.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1085.pdf


    946. Experimental investigation of the positions of the leading-edge vortices above slender delta wings with various rhombic cross-sections in subsonic conical flow

    D. L. I. Kirkpatrick and J. D. Field
    ARC/CP-925
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0925.pdf


    947. Flight and tunnel measurements of pressure fluctuations on the upper surface of the wing of a Venom aircraft with a sharpened leading-edge

    R. Rose, O. P. Nicholas
    ARC/CP-1032
    November 1967

    Part span sharpened leading-edges were attached to the wing to produce regions of separated flow. Flight measurements were made of both the spectra and root-mean-square intensity of the pressure fluctuations at orifices at 1% and 60% of the local chord. Corresponding measurements on a model in a low speed wind tunnel covered a wider range of incidence and frequency than the flight tests. The flight test results are in good agreement with the tunnel results. The root-mean-square value of the pressure fluctuations, p, reached a maximum value of p/q = 0.072 for the 60% orifice at an incidence of 10 degrees. The incidence for buffet onset was close to that at which the break in the p/q vs. a curves for both orifices occurred.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1032.pdf


    948. Forces on cone cylinders at M = 3.98

    K.C. Moore
    ARC/CP-1016
    November 1967

    Normal force and pitching moment have been measured on a number of cone cylinder combinations at a Mach number of 3.98 in the 3 ft x 4 ft High Supersonic Speed Tunnel. The results are presented graphically. Comparison is made with theoretical predictions for the same quantities at small incidence based on second order generalized shock expansion theory, and with semi-empirical estimates based on the Data Sheets of the Royal Aeronautical Society.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1016.pdf


    949. Free-flight measurements of the incremental drag due to engine nacelles on a transonic swept-wing aircraft

    G. K. Hunt
    ARC/CP-960
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0960.pdf


    950. Free-flight tests in the NPL 6-in. (15-cm) shock tunnel of model HB-2 using multiple spark recording

    L. Pennelegion, R. F. Cash and M. J. Shilling
    ARC/CP-934
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0934.pdf


    951. Heat transfer in the vicinity of a 15 degrees compression corner at mach numbers from 2.5 to 4.4

    R. C. Hastings, C. S. Brown, Susan Atkinson
    ARC/CP-965
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0965.pdf


    952. Investigation of the normal force characteristics of slender delta wings with various rhombic cross-sections in subsonic conical flow

    D. L. I. Kirkpatrick
    ARC/CP-922
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0922.pdf


    953. Laminar boundary layer calculations compared with measurements by hummel

    J.C. Cooke
    ARC/CP-1096
    September 1967

    Calculations by an integral method assuming small cross-flow, and by a finite-difference method assuming the flow to be quasi-conical, are compared with measurements made available by Hummel (Technical University, Brunswick) on a highly swept delta wing at high incidence. It is found that the small-cross-flow method gives a rough general picture of the flow but is inaccurate in the details, especially velocity profiles. For this problem the quasi-conical method is more accurate over most of the flow field and gives a much better representation of the velocity profiles.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1096.pdf


    954. List of current papers (numbers 801-850)

    Aeronautical Research Council
    ARC/CP-850
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0850.pdf


    955. List of current papers (numbers 851-900)

    Aeronautical Research Council
    ARC/CP-900
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0900.pdf


    956. List of current papers (numbers 901-950)

    Aeronautical Research Council
    ARC/CP-950
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0950.pdf


    957. Low speed flight tests on a tailless delta wing aircraft (Avro 707B) Part 2. longitudinal stability and control

    W. G. A. Port, J. C. Morrall
    ARC/CP-1105
    August 1967

    Flight tests have been made to measure the static and dynamic longitudinal stability, the effect of ground on stability, and the elevator power of the Avro 7078 which has a delta wing sweptback 44.5 degress. A comparison of the results with those of tunnel tests is made. There is a loss of static stability, stick fixed and free, above a lift coefficient of 0.5. Stick force/g at low speed is small particularly at the aft og position, although no great difficulties were encountered due to this or the lack of static stability during the approach and landing.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1105.pdf


    958. Low speed wind tunnel tests on a series of rectangular wings of varying aspect ratio and aerofoil section

    G. G. Brebner, L. A. Wyatt, Gladys P. Ilott
    ARC/CP-916
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0916.pdf


    959. Low-speed measurements of skin friction on a large half-model slender wing

    L. A. Wyatt, L. F. East
    ARC/CP-1007
    August 1967

    Skin-friction measurements have been made on a half-model slender wing of 24 ft root chord at low subsonic speeds. The maximum root-chord Reynolds number was 30 x 10power6. The measurements were made using surface pitot-tubes formed by magnetically attaching razor-blade segments to the model surface. The results show that high levels of skin friction are present beneath the leading-edge vortex and are correlated satisfactorily with previous results obtained at lower Reynolds numbers.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1007.pdf


    960. Low-speed wind-tunnel measurements of damping in yaw (n psi) on an aspect ratio 9 jet-flap complete model

    A. P. Cox and S. F. J. Butler
    ARC/CP-869
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0869.pdf


    961. Measurement of the internal drag of air breathing installations on slender wing-body combinations at supersonic speeds

    J. W. Britton
    ARC/CP-914
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0914.pdf


    962. Measurement of the moments of inertia of the handley page HP115 aircraft

    L. J. Fennell
    ARC/CP-907
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0907.pdf


    963. Measurements of buffeting on slender wing models

    D. G. Mabey
    ARC/CP-917
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0917.pdf


    964. Measurements of drag, base pressure and base aerodynamic heat transfer appropriate to 8.5 degrees semi-angle sharp cones in free flight at mach numbers from 0.8 to 3.8

    G. H. Greenwood
    ARC/CP-958
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0958.pdf


    965. Measurements of pressure distribution and shock-wave shape on power-law bodies at a mach number of 6.85

    D.H. Peckham
    ARC/CP-871
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0871.pdf


    966. Measurements of wing buffeting on a scimitar model

    D. G. Mabey
    ARC/CP-954
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0954.pdf


    967. More tests with a variable ramp intake having a design mach number of 2.2

    M. C. Neale and P. S. Lamb
    ARC/CP-938
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0938.pdf


    968. Nitrogen condensation in the R.A.R.D.E. hypersonic gun tunnel

    J. E. Bowman
    ARC/CP-956
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0956.pdf


    969. On the breakdown of near-equilibrium quasi-one-dimensional flow

    P. A. Blythe
    ARC/CP-923
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0923.pdf


    970. On the flexure of a conical frustum shell

    E. H. Mansfield
    ARC/CP-1039
    October 1967

    This Report considers theoretically and experimentally some of the problems associated with the flexure of two unequal cylindrical shells Joined by a conical frustum. Particular attention is given to the determination of the overall flexural stiffness of the conical frustum and to structural design considerations associated with the provision of a separation capability in the frustum. The results are particularly relevant to the design of multistage rockets.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1039.pdf


    971. Potential flow theory for tandem cascade by Howell's method

    Y. M. Yip and J. W. Railly
    ARC/CP-971
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0971.pdf


    972. Preliminary flight assessment of the low-speed handling of the BAC 221 ogee-wing research aircraft

    C. S. Barnes, O. P. Nicholas
    ARC/CP-1102
    November 1967

    The handling of the BAC 221 slender-ogee-wing research aircraft, at speeds down to 114 knots ias and incidences up to 22°, is described. Pilots considered the aircraft handling as pleasant, in general. The mayor problems were of lateral/directional control at high angles of incidence when difficulty was experienced in preventing large sideslip angles from building up. At all angles of incidence in the low-speed range, the response to aileron was oscillatory. Reducing the effective adverse aileron yaw of the aircraft by an interconnect, enabling the ailerons to drive the rudder, lessened the difficulties in sideslip control and the oscillatory response to aileron inputs was reduced. Longitudinal control was good, but at a = 22° a mild pitch-up occurred. Aerodynamic buffet increased at this incidence and vortex bursting is thought to have reached forward to the rear parts of the wing. Although approaches were made well below the minimum drag speed, speed control presented no difficulty, provided that it could be given full attention. Cross-wind take-offs and landings presented no problems except during the ground run. Side-step manoeuvres on the approach were made with no difficulty.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1102.pdf


    973. Project topcat power spectral measurements of clear air turbulence associated with jet streams

    Anne Burns, C. K. Rider
    ARC/CP-940
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0940.pdf


    974. Random and systematic factors in the scatter of creep data

    K. F. A. Walles
    ARC/CP-935
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0935.pdf


    975. Short-cowl front-fan turbojets friction drag and wall-jet effects on cylindrical afterbodies

    J. E. Green
    ARC/CP-1049
    June 1967

    An approximate analysis is given of a turbulent wall-jet beneath a stream moving at constant velocity. The results of this analysis are used to predict the drag of a cylindrical afterbody immersed in the jet from a front fan with short cowl at subsonic flight speeds. Graphs are presented which allow rapid evaluation of afterbody drag for a range of jet pressure ratios and nacelle geometries.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1049.pdf


    976. Some comments on the conditions in a local supersonic flow region

    T. H. Moulden
    ARC/CP-1023
    January 1967

    The paper sets out to summarise the properties of the flow in a local supersonic, two-dimensional, steady potential flow region. Starting from the results of the theory of characteristics, the concept of wave strength is introduced and used to develop logically the properties of the supersonic region. The conditions which must be imposed on the flow in order that it shall remain irrotational are reviewed. The practical significance of this is mentioned.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1023.pdf


    977. Some exploratory tests on a two-dimensional blown-cylinder model in the R.A.E. 2 ft x 1.50 ft transonic-wind tunnel

    A. F. Jones, W. R. Buckingham
    ARC/CP-889
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0889.pdf


    978. Some further notes on the laminar boundary layer development and running time in a shock tube

    J. A. D. Ackroyd
    ARC/CP-966
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0966.pdf


    979. Some notes on fuel boiling losses and fuel-tank pressurisation in a long-range supersonic aircraft

    W. G. S. Lester
    ARC/CP-1017
    June 1967

    A method of calculating the fuel boiling losses, due to aerodynamic heating, from a supersonic aircraft with integral wing fuel tanks is devised and is applied to the Concord, assuming flight conditions of Mach 2.2 at 64000 ft altitude using low boiling point kerosene fuel. It is shown that if the specified tank pump performance is achieved the quantity of fuel evaporated is no more than 150 lb if the tanks are unpressurised, and is negligible in the present design case where the tanks are pressurised. to 2.2 psia. The calculations are based on certain assumptions defined in the text concerning fuel distillation characteristics, heat transfer data and boiling fuel distribution in the tankage. Because much of the evaporated fuel may condense in the vent system and be recovered it is likely that the fuel loss through boiling in unpressurised tanks will be less than the weight of additional equipment required to pressurise the tanks. Since the fuel transfer pump duty is very arduous, the feasibility of operating without tank pressurisation depends on the actual pump performance achieved. Suggestions are made for reducing the severity of the conditions affecting fuel thermal stability by modified fuel handling procedures in the aircraft. Note (added April 1968) The Concord performance specifications and fuel system design have been changed since this Report was issued originally and the numerical values quoted for fuel losses, based as they are on the data available in 1967, are no longer applicable to the actual aircraft.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1017.pdf


    980. Some tests with a variable ramp intake having sidewall compression and a design mach number of 2.2

    M. C. Neale and P. S. Lamb
    ARC/CP-936
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0936.pdf


    981. Some theoretical studies concerning oleo damping characteristics

    H. Hall
    ARC/CP-951
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0951.pdf


    982. Stability and control flight testing - some of the test instrumentation requirements

    R. Rose
    ARC/CP-1015
    May 1967

    The scope of stability and control flight testing at R.A.E. Bedfold and the type of physical measurements are briefly reviewed. Suggested overall accuracies for the quantities, including the effects of transducer/recording element and readout system, are stated. Particular emphasis is put on the need for good instrumentation dynamic characteristics and the need for accurate dynamic calibrations of the instruments. The overall accuracies achieved using photographic trace recording systems is of the order 2% - 3%, whilst 1% is required and exceptionally, for special tests, 0.2%. The use of digital/magnetic tape systems looks attractive to meet these requirements, but flight experience has shown that the potential accuracy of ths system may not be achieved. The need for proving new sophisticated instrumentation systems in real flight environments is stressed. Paper prepared for the Thirtieth AGARD Flight Mechanics Panel on Flight Test Instrumentation - Montreal, Canada.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1015.pdf


    983. Stiffness, damping and creep properties of a polyurethane foam including the effects of temperature and humidity

    D. B. Payen
    ARC/CP-905
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0905.pdf


    984. Studies of flow fields created by vertical and inclined jets when stationary or moving over a horizontal surface

    W. A. Abbott
    ARC/CP-911
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0911.pdf


    985. Studies of the flow fields created by single vertical jets directed downwards upon a horizontal surface

    M. Cox and W. A. Abbott
    ARC/CP-912
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0912.pdf


    986. Supersonic flutter derivatives for a series of swept and cropped delta wings

    G.Z. Harris
    ARC/CP-920
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0920.pdf


    987. Symposium on the use of the digital computer in aircraft structural design and analysis

    G. G. Pope
    ARC/CP-926
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0926.pdf


    988. Techniques for tests on structures subject to kinetic heating

    P. Talbot
    ARC/CP-970
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0970.pdf


    989. Tests at M = 1.82 on an engine installation with boundary-layer diverter for a slender gothic wing

    R. T. Griffiths, E. L. Goldsmith
    ARC/CP-1059
    August 1967

    This Paper should be read in conjunction with A.R.C.26912 (C.P. 866) The absolute values of the results obtained do not have a great significance. Their main interest lies in their relationship to those of C.P. 866. In these two Papers there is effectively an aerodynamic performance comparison between two philosophies of engine installation. In C.P. 866 the objective was to bury the excess area between intake entry and engine maximum cross section in the local wing structure and hence produce (within the limitations of a fixed geometry intake with all-external compression) a low drag installation. In the tests described in the present Paper no attempt was made similarly to bury this excess area when the engines were mounted four in a square per nacelle and hence it was realised that the installation would lead to high wave drag. The pressure field from the cowl forebody was then used to interfere favourably (in a lift and drag sense) with the undersurface of the wing in an effort to offset this high cowl wave drag. This philosophy was particularly accentuated in this model by the choice of short length for both forebody and afterbody of the nacelle. The particular balance desired and achieved when using pressure fields, that produce drag, also to produce lift, is a delicate one (see R & M 3528) and the results of this investigation show that this particular design was probably quite far from the optimum arrangement.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1059.pdf


    990. Tests on an engine installation for a slender gothic wing at M = 1.82

    R. T. Griffiths
    ARC/CP-866
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0866.pdf


    991. Tests with a two-dimensional intake having all-external compression and a design mach number of 2.0

    M. C. Neale and P. S. Lamb
    ARC/CP-937
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0937.pdf


    992. Tests with a two-dimensional intake having all-external compression and a design mach number of 2.2

    M. C. Neale and P. S. Lamb
    ARC/CP-939
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0939.pdf


    993. The accuracy of pressure transducers when used in short-duration wind tunnel facilities

    L. Pennelegion, K. Wilson and B. Redston
    ARC/CP-949
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0949.pdf


    994. The application of non-dimensional methods to the planning of helicopter performance flight trials and the analysis of results

    P. A. Knowles
    ARC/CP-927
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0927.pdf


    995. The breakdown of certain types of vortex

    N. C. Lambourne
    ARC/CP-915
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0915.pdf


    996. The calculation of momentum thickness in a turbulent boundary layer at mach numbers up to unity

    J. F. Nash and A. G. J. Macdonald
    ARC/CP-963
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0963.pdf


    997. The calculation of the pressure distribution on a thick cambered aerofoil at subsonic speeds including the effects of the boundary layer

    B. J. Powell
    ARC/CP-1005
    June 1967

    This Paper describes a method for calculating the pressure distribution on the surface of a two-dimensional aerofoil of arbitrary shape in subsonic flow, taking into account the presence of a boundary layer on the surface of the aerofoil. The effect of the boundary layer is accounted for by considering the inviscid flow over a displacement surface made up of the aerofoil section shape, boundary layer displacement thickness and. the wake. A simple model of the wake is introduced, and it is shown that provided certain simple conditions are satisfied in the region near the aerofoil trailing edge, the pressure distribution predicted is not unduly sensitive to the detailed development of the wake. The method has been developed using techniques which make it very suitable for computation on a digital computer. Calculations have been made of the pressure distribution on a RAR 101 aerofoil section at incidence for which measured boundary layer data were available, and also in the ease of a heavily cambered. aerofoil at incidence using theoretically predicted boundary layer characteristics. The comparison between the experimental. and predicted pressure distributions shows good agreement in both cases.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1005.pdf


    998. The derivation of power spectra of density variations in hypersonic wakes from schlieren photographs

    J. P. Thompson
    ARC/CP-1021
    September 1967

    An analysis is given of the relationship between power spectra of image density variations in a schlieren film of a hypersonic wake and the power spectra of gas density variations in the wake. Some results are given for the application of this theory to the schlieren film produced in an R.A.R.D.E. hypervelocity range test.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1021.pdf


    999. The development at Cranfield of a free piston compression shock tube

    M.J. Pratt
    ARC/CP-1002
    February, 1967

    The free piston compression shock tube provides a simple means of obtaining shock Mach numbers of the order of 30. This paper concerns the design and development at Cranfield of such a shock tube. The problems encountered in evolving a piston capable of withstanding heavy impacts at the completion of its stroke are outlined, and some preliminary shock tube performance data given.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1002.pdf


    1000. The distribution of a wall pressure rise in a turbulent boundary layer

    R.J. Herd
    ARC/CP-967
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0967.pdf


    1001. The drag of some wedge centre-body intakes at mach numbers of 1.56, 1.86 and 2.14

    R. A. Dutton, E. L. Goldsmith
    ARC/CP-968
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0968.pdf


    1002. The effect of base bleed on the base pressure of several shrouded and unshrouded propelling nozzles at M = 1.96

    M.M. Shaw
    ARC/CP-962
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0962.pdf


    1003. The effects of extended practice on performance in a tracking task

    R.C. Hornby and R. Wilson
    ARC/CP-1030
    December 1967

    Experimental measurements of human controller performance have been made during extended periods of practice in visual sine-wave tracking tasks. It has been found that, irrespective of task difficult, RMS error scores decreased to such small magnitudes that differences in scores due to different task variables would have no practical significance. Thus the averaged values of steady scores when tasks are well learnt are meaningless for subject or task difficulty comparisons. It has been shown that the performance scores vary in an exponential manner with the number of task repetitions and it is proposed that an empirical constant related to the rate of decrease of scores be used as a measure of relative task difficulty.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1030.pdf


    1004. The influence of density gradients on the effectiveness of film cooling

    B. R. Pai and J. H. Whitelaw
    ARC/CP-1013
    December 1967

    New measurements of the impervious-wall effectiveness are presented in the range of the velocity ratio ... These measurements were carried out using hydrogen, air, argon and Arcton 12 as the injected gas: the resulting range of density ratios was ... The measurements demonstrate, quantitatively, that an increase in the density ratio leads to an increase in effectiveness for the same velocity ratio. The prediction method proposed by S. V. Patankar and D. B. Spalding has been tested against the present measurements and shown to be a convenient method in the region downstream of the immediate vicinity of the slot exit. The predictions are reasonable but it is concluded that further experimental work is necessary to establish the appropriate distribution of the effective Schmidt (or Prandtl) number.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1013.pdf


    1005. The influence of gas streams and magnetic fields on electric discharges part 3 arcs in transverse magnetic fields at atmospheric pressure

    V. W. Adams
    ARC/CP-959
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0959.pdf


    1006. The interaction of the reflected shock with the boundary layer in a shock tube and its influence on the duration of hot flow in the reflected-shock tunnel part 2

    L. Davies
    ARC/CP-881
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0881.pdf


    1007. The Longitudinal Characteristics of Three Slender "Mild Ogee" Wings at Mach Numbers from 0.4 to 2.0

    D.G. Mabey, G.P. Ilott
    ARC/CP-1006
    August 1967

    Wind tunnel measurements of lift, pitching moment and drag on one plane and two cambered wings of "mild ogee" planfom (p = 8/15) are reported. These measurements are supplemented by vapour screen and oil flow observations. The wings were designed by slender wing theory for attached flow along the leading-edge at particular values of lift and pitching moment. The design and measured attachment conditions agreed fairly well. The non-linear lift developed could be related with the type of vortex development above the attachment incidence.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1006.pdf


    1008. The performance of an aerofoil in stationary and rotating cascades

    E. C. Deverson, H. Marsh and J. T. B. Oxford
    ARC/CP-1022
    April 1967

    A series of experiments have been performed with a rotating cascade wind tunnel to determine the effect of a rotational flow on the behaviour of the blades in a turbomachine. A two-bladed rotor has been tested as a stationary annular cascade - and also when rotating synchronously with a solid body rotational flow. It is then possible to make a direct comparison between the behaviour of the same blade in irrotational and rotational flows. It is shown that if the level of turbulence is greater than some critical value, then there is no significant difference in the unstalled performance of the blades in the stationary and rotating cascades. However, even at a relatively high level of turbulence, there is a marked difference in the manner in which the blade stalls for the stationary and rotating cascades.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1022.pdf


    1009. The pressure drag of an aerofoil with six different round leading edges, at transonic and low supersonic speeds

    P. G. Wilby
    ARC/CP-921
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0921.pdf


    1010. The Range Performance of Hypersonic Aircraft

    D. H. Peckham and L. F. Crabtree
    ARC/CP-932
    June 1966

    A simple analysis is given of the range performance of hypersonic aircraft. Some relatively crude approximations are used to enable the range covered during acceleration and final glide, which can be a considerable fraction of the total range, to be taken into account.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0932.pdf


    1011. The spectral energy balance in a turbulent mixing layer

    P. Bradshaw and D. H. Ferriss
    ARC/CP-899
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0899.pdf


    1012. The thermal assessment of personal conditioning garments

    D. R. Burton
    ARC/CP-953
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0953.pdf


    1013. The velocity field near non-lifting delta wings according to supersonic linearized theory

    R. S. Bartlett
    ARC/CP-961
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0961.pdf


    1014. Thermal conductance tests on cabin wall insulation assemblies for a supersonic transport aircraft

    Ian I. McNaughtan and P. A. Keene
    ARC/CP-910
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0910.pdf


    1015. Viscosity effects on the two-dimensional flow in cascades

    J. P. Gostelow, A. K. Lewkowicz and M. R. A. Shaalan
    ARC/CP-872
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0872.pdf


    1016. Wind tunnel measurements of the effect of a jet on the time average and unsteady pressures on the base of a bluff afterbody

    J.E. Rossiter, A.G. Kurn
    ARC/CP-903
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0903.pdf


    1017. Wind tunnel tests on a rectangular, twin duct, variable geometry air intake at supersonic speeds

    M. D. Dobson
    ARC/CP-944
    1967

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0944.pdf


    1018. Wind tunnel tests on six wing-body models at M = 4

    J. Pike
    ARC/CP-1074
    August 1967

    Force measurements and flow patterns for six models, with the same ogive-cylinder body and various wings, are presented for a free streem Mach number of 4. Five of the wings were unswept, and the sixth was a 65° delta. Values of CL, CM and CD are compared for models of different wing section, aspect ratio and taper ratio. They are also compared with values from the same models tested at lower Mach numbers.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1074.pdf


    1019. A control and measurement system for aeroelastic model tests

    W. D. T. Hicks
    ARC/CP-1045
    September 1968

    A semi-automatic data handling system has been constructed at the R.A.E. for use in wind tunnel and laboratory tests on aeroelastic models. The system can accept fifty inputs of static information and fifty oscillatory inputs; the latter can be analysed to yield the components of each input that are in-phase and in-quadrature with a sinusoidal reference signal. The system can be programmed to handle, automatically, sequences of input data and, after analysis, to output the data in printed form and on punched paper tape. Graphical presentation of analysed oscillatory data is provided. The equipment has been used in several wind tunnel test programmes resulting in an economical use of wind tunnel test time and skilled manpower.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1045.pdf


    1020. A critical examination of the use of a two-dimensional turbulent profile family to represent three-dimensional boundary layers

    N.A. Cumpsty
    ARC/CP-1068
    December 1968

    The streamwise velocity profile is established as the most suitable basic profile for the calculation of three-dimensional turbulent boundary layers. Measured streamwise profiles are compared with Thompson's two-dimensional profile family and it is shown that the discrepancies produced by the variation of flow direction within the boundary layer, the pressure gradient normal to the external flow and the convergence or divergence of the flow are generally small. The result of the streamwise pressure gradient (which is as much a two-dimensional as a three-dimensional effect) can, however, be very appreciable. The four effects listed above are expressed as non-dimensional parameters and limits are suggested within which the streamwise profile is likely to be moderately well represented by Thompson (or similar) two-dimensional profiles. Some consideration is given to the associated problem of estimating the coefficient of skin friction in three-dimensional boundary layers and some alternative methods are compared.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1068.pdf


    1021. A marching procedure for the determination of inviscid two-dimensional sonic flow past a blunt symmetrical body

    D. G. Randall
    ARC/CP-992
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0992.pdf


    1022. A method for the prediction of the probabilities of aircraft fatigue failures within a fleet of known size

    A. M. Stagg
    ARC/CP-1033
    July 1968

    An algebraic solution is given for the problem of ascertaining the probability of finding any number of fatigue cracks in a fleet of aircraft at any specific point in time. By a simple approximation concerning the fatigue damage incurred by the members of the fleet the solution is simplified into a working method for the determination of the aforesaid probability. With two parameters arbitrarily chosen, results are given to illustrate the nature of the solution.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1033.pdf


    1023. A Note on some Static Tests of Flexible Skirts for Hovercraft

    W. G. S. Lester ond F. T. Kiernan
    ARC/CP-990
    February 1966

    A series of static tests ccnducted to establish an efficient form of flexible skirt for a peripheral Jet type of hovercraft is reported. The importance of designing the peripheral Jet system in conjunction with the skirt is demonstrated. The results suggest that the effective width of a flexible nozzle 1s less than its actual with and the discharge coefficient requires determining experimentally for each configuraticn. It is concluded that skirt confiquration performance is best compared on the basis of power input to a skirt to generate a given cushion pressure fcr a specified daylight clearance.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0990.pdf


    1024. A piloted flight simulator study of speed instability during the landing approach

    D.H. Perry
    ARC/CP-980
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0980.pdf


    1025. A survey of fluid flow and heat transfer in rotating ducts

    Henry Barrow
    ARC/CP-1054
    September 1968

    This Paper is intended as an introduction to the study of fluid flow and heat transfer in rotating ducts, and to serve as a basis for discussion of this field of work. The interest in this subject results mainly from the need to determine heat transfer between the surfaces of ducts or passages in the components of rotating machines and a confined or flowing fluid. There are numerous situations in the engineering field where this type of problem occurs.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1054.pdf


    1026. A survey of the infrared radiation properties of carbon dioxide

    J. P. Hodgson
    ARC/CP-981
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0981.pdf


    1027. A survey of the thermal conductance of metallic contacts

    H. Y. Wong
    ARC/CP-973
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0973.pdf


    1028. A theoretical investigation for delta wings with leading-edge separation at low speeds

    R. K. Nangia and G. J. Hancock
    ARC/CP-1086
    August 1968

    A non-linear lifting surface theory is postulated which incorporates the leading edge separations, by extending Brown and Michael's slender wing model, but satisfies the Kutta trailing edge condition. Results of a numerical application to a delta wing indicate acceptable trends compared with experimental data.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1086.pdf


    1029. A wind-tunnel investigation of the stalling performance of two compressor cascades of different aspect ratios at low speed

    M. R. A. Shaalan
    ARC/CP-1103
    March 1968

    Two compressor cascades of aspect ratio 2.10 and 4.83 were tested up to the stall point in a working section with solid side walls. A change in aspect ratio was obtained by changing the blade chord only. The blade section profile was the 10C4/30C50, staggered at 36 degrees with a space-chord ratio of 0.88, and there was no tip clearance. Reynolds number similarity was maintained but its value was kept above a "critical" value. Substantial difference in performance is indicated between the two aspect ratios. The high aspect ratio cascade gives more deflection at the mid-span near stall, but stalls first. The long chord, low aspect ratio blade stalls gently whilst a classical type of sudden stall occurs at the other aspect ratio. Higher pressure rise coefficient is observed at the high aspect ratio, increasing slightly with incidence up to the stall point. Substantially higher spanwise contraction is evident with the low aspect ratio. The order of magnitude of the increase in axial velocity for both cascades is remarkably high. Further tests show that the wall stall, which is present at each incidence, is different in the two cases. It appears that the flow near the wall in the long chord blade rotates further in the passage and the stall near the end wall is more along the blade than along the wall. In the case of the short chord, the separation areas along the blade and the wall are approximately equal. The results for the overall performance are generally consistent with compressor work.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1103.pdf


    1030. An experimental investigation of laminar heat transfer in a uniformly heated tube rotating about a parallel axis

    W. D. Morris
    ARC/CP-1055
    September 1968

    The results of an experimental investigation which studies the influence of rotationally induced buoyancy on heat transfer in a tube which rotates about an axis parallel to itself is presented. Data obtained with water and 100% glycerol appear to confirm the qualitative description of flow given by two theoretical analyses. A reliable qualitative method of prediction is still unavailable.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1055.pdf


    1031. An investigation of the rolling moments due to sideslip on high tailplanes at subsonic, transonic and supersonic speeds

    D. G. Mabey
    ARC/CP-999
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0999.pdf


    1032. Atmospheric gusts a review of the results of some recent R.A.E. research

    J. Burnham
    ARC/CP-1091
    October 1968

    Recent R.A.E. research on gusts has been particularly concerned with severe gusts and the situations in which they occur. In the stratosphere, mountain wave conditions and those in the vicinity of thunderstorm tops have been investigated. At lower altitudes, gusts in and near thunderstorms have also been studied, as have wind and gust effects likely to be significant during take-off and landing. This work has relevance both to aircraft operations and to aircraft design. In the latter connection, recent work on mathematical models of severe gusts is also described. Mention is made of the effects of pilot control activity during flight through gusts.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1091.pdf


    1033. Cabin air requirements for crew comfort in military aircraft

    T. L. Hughes
    ARC/CP-1094
    December 1968

    The Report discusses the effect of various parameters, relating to the crew and aircraft, on cabin air supply requirements for crew comfort. A method of presenting the relationships between the various parameters in the form of 'design curves' is shown. The validity of these is discussed and recommendations made where further confirmatory evidence is required. Using the 'design curves' and a computer program, the relative importance of factors influencing cabin air requirements for comfort have been examined and recommendations made on how cockpit conditions might be improved.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1094.pdf


    1034. Cabin conditioning tests on a simulated M 2.2 transport aircraft cabin

    T. L. Hughes, E. A. Timby
    ARC/CP-976
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0976.pdf


    1035. Calculation of the response of a transport aircraft to continuous turbulence and discrete gusts and a comparison with flight measurements

    C. G. B. Mitchell
    ARC/CP-1035
    April 1968

    The symmetric response of a tri-jet transport aircraft to continuous atmospheric turbulence and to discrete ramp gusts has been calculated and compared with the results of flight measurements. The aircraft was represented by two rigid and six elastic modes, and a lifting surface theory was used to calculate airforces. Cockpit and wingtip rms accelerations relative to the cg acceleration were overestimated by the calculations, but wing end tailplane rms bending moments per g agreed with measurements to better than 12% accuracy.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1035.pdf


    1036. Civil aircraft airworthiness data recording programme special events relating to airspeed control and handling (February 1966 to December 1967)

    CAADRP Special Events Working Party, G. E. King
    ARC/CP-1051
    August 1968

    A small number of jet aircraft in normal airline service are fitted with recorders which produce continuous trace records of airworthiness data for 14 parameters. Throughout the recording period the records have been searched for unusual occurrences, and each one has been studied to determine its nature and, where possible, its cause. This Report describes a selection of events relating to airspeed control and handling which were found in records taken between February 1966 and December 1967.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1051.pdf


    1037. Comparison of different methods of assessing the free oscillatory characteristics of aeroelastic systems

    A. Jocelyn Lawrence, P. Jackson
    ARC/CP-1084
    December 1968

    Different approximate methods of determining the eigenvalues of the integro-differential matrix equation of a simple aeroelastlc system are compared. It is shown that methods which use an approximate second order differential matrix equation with constant coefficients can give large errors in the values of complex eigenvalues, though the errors are usually small at airspeeds below the critical flutter speed, if the frequency parameter of each particular eigenvalue is lined-up with the value used to determine the aerodynamics. An improved method of solution using a finite series approximation to the indicial aerodynamics yielded in some cases an additional complex eigenvalue with a frequency of the same order as the other natural frequencies.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1084.pdf


    1038. Correlation of voltage-current characteristics of wall-stabilised, free-burning and cross-flow arcs

    W. T. Lord
    ARC/CP-996
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0996.pdf


    1039. Crossflow in turbulent boundary layers

    N. A. Cumpsty
    ARC/CP-1067
    December 1968

    Two well known representations for the crossflow velocity profile, due to Mager and Johnston, are discussed, and limitations to their applicability are outlined. A number of ideas relating to the Johnston triangular model are discussed and a method for extending its usefulness is presented. Finally an approach which should lead to a prediction of the form of cross-over crossflow profiles (where the sign of the crossflow changes through the depth of the layer) is described. The predictions are shown to be consistent with the available measured profiles.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1067.pdf


    1040. Design of a symmetrical section with specified pressure distribution

    C. C. L. Sells
    ARC/CP-1047
    May 1968

    A method for the calculation of the section thickness distribution to produce a given symmetrical pressure distribution near the critical Mach number is presented. By linearisation about a known solution, obtained by Sells' program, a Neumann problem with the ssme field equations but a different boundary condition is established, and the computer solution of this problem forms one link in an iteration sequence. In the symmetrical case studied, the sequence converged to a slightly different solution from that sought. Attempts at solution of the lifting problem have been unsuccessful.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1047.pdf


    1041. Discrete element analysis of the lateral vibration of rectangular plates in the presence of membrane stresses

    D. J. Dawe
    ARC/CP-1062
    September 1968

    The discrete element displacement method is applied to the prediction of the natural frequencies of lateral vibration of rectangular plates which may be subjected to arbitrary systems of in-plane loading. Numerical results are given for several problems in which the applied stress system is uniform and these results are shown to be in good agreement with available solutions.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1062.pdf


    1042. Drag measurements on a series of afterbodies at transonic speeds showing the effect of sting interference

    A. G. Kurn
    ARC/CP-984
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0984.pdf


    1043. Experiments on methods for the numerical solution of a certain non-linear biharmonic equation

    M. R. Abbott
    ARC/CP-979
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0979.pdf


    1044. Finite difference solutions for an unsteady interference parameter in slotted wind tunnels

    K.R. Rushton and Lucy M. Laing
    ARC/CP-1053
    OCtober 1968

    Three methods of determining an unsteady interference parameter in slotted wind tunnels are described. In each case the governing equation for the flow in the wind tunnel is Laplace’s equation which is solved by a finite difference approximation. The methods differ in the representatIon of the disturbance due to the wing. A discussion of the merits of each method is included, results are quoted for tunnels of square section with roof and floor of varying slot parameter.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1053.pdf


    1045. Flight measurements of wing-tip vortex motion near the ground

    F.W. Dee, O.P. Nicholas
    ARC/CP-1065
    January 1968

    Tests have been made to measure the movement of the wing tip vortices from a Hunter aircraft flying at 170 knots approximately 35 feet above a runway, in a variety of wind conditions. Measurements were limited to a maximum time of 20 seconds after vortex generation. During the period the theoretical predictions presented are in good general agreement with the observed motions; however significant differences did occur. There was no clear indication as to whether the vortices decayed more rapidly in the presence of the ground and atmospheric turbulence, than would have been expected from earlier measurements away from the ground in calm air. Limited tests were also made to study the vortex mutual interaction away from the ground.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1065.pdf


    1046. Free flight measurements of the longitudinal stability of a transonic swept-winged aircraft

    G. K. Hunt
    ARC/CP-1052
    July 1968

    Four models of an aircraft configuration with a 55 degree swept wing were flown at Mach numbers between 0.9 end 1.4, at Reynolds numbers up to 10 million and lift coefficients between zero and 0.5. Measurements of the manoeuvre margin and the derivatives ... were obtained. The results are compared with those obtained from one of the same models in a transonic wind tunnel and from a related M-wing model in flight. They are also corrected for aeroelastic effects.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1052.pdf


    1047. Further analysis of TSR 2 flights through turbulence

    T.B. Saunders
    ARC/CP-997
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0997.pdf


    1048. Gradient properties of a model of stationary random turbulence

    J. G. Jones
    ARC/CP-998
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0998.pdf


    1049. Guided weapons aerodynamic study force and moment measurements on some monoplane and cruciform slender wing-body combinations at M 4. 0

    P. L. Roe
    ARC/CP-972
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0972.pdf


    1050. Heat transfer in a tube revolving about a displaced axis

    J.F. Humphreys
    ARC/CP-1069
    October 1968

    Consideration is given to heat transfer and fluid flow in the entry region of a tube revolving about a displaced axis parallel to the tube axis. Experimental results indicate that both inherent swirling flow and centrifugal buoyancy contribute to increases in heat transfer as a result of rotation.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1069.pdf


    1051. Inflated mobile lifting structures practical design and trials of a circular planform model using membrane construction

    A. Y. Simpson
    ARC/CP-1056
    June 1968

    Early lifting structures and planforms With two straight sides and circular ends and with many lifting points in order to encompass road vehicles economically. Problems of load slinging and structural inflexibility, however, precluded the use of the system for most practical applications. This paper describes tests carried out on a circular-planform model to ascertain the effect on performance of only four load attachment points. After several modifications, a practical design was evolved, for use as a basis for a full scale prototype. Appendix B includes a posSible application for such a device.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1056.pdf


    1052. Leading edge effects on caret wings

    J. C. Cooke
    ARC/CP-978
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0978.pdf


    1053. List of Current Papers (Numbers 1051-1100)

    Aeronautical Research Council
    ARC/CP-1100
    1968

    This paper lists fifty titles which have been published in the CP Series of the Aeronautical Research Council.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1100.pdf


    1054. Loads experienced in turbulence by a central African airways viscount without and with cloud warning radar

    N.I. Bullen, Judy E. Aplin
    ARC/CP-1038
    March 1968

    Counting accelerometer records were obtained from a Central African Airways Viscount. After a year's recording, cloud warning radar was fitted to the aircraft and data for a further three years were obtained. A comparison is made between the loads experienced during the two periods and it is concluded that the carrying of radar has little effect on fatigue damage, but considerably reduces the frequency of high loads, at 1 g the reduction being by a factor of six.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1038.pdf


    1055. Low-speed wind-tunnel investigation of the roll stability of a .20 scale model of the short SC 1 at large sideslip

    W. J. G. Trebble
    ARC/CP-994
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0994.pdf


    1056. Low-speed wind-tunnel tests of a number of fin configurations on a flat-plate gothic wing of unit aspect ratio

    D. H. Peckham
    ARC/CP-1076
    November 1968

    Results are given of six-component balance measurements on a gothic wing of unit aspect ratio fitted either with a pair of fins, at various spanwise locations, or a single central fin. Each fin was triangular in shape, with a leading-edge sweep of 60 degrees and an area 12.5% of chat of the wing.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1076.pdf


    1057. Low-speed wind-tunnel tests on a 1/6th scale model of an air-cushion-vehicle (Britten-Norman cushioncraft C.C.2.)

    W.J.G. Trebble
    ARC/CP-983
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0983.pdf


    1058. Measurements of fluctuating pressures in and behind the bomb bay of a Canberra Aircraft

    C. W. Skingle, N. M. Willcox, D. R. Gaukroger
    ARC/CP-1025
    April, 1968

    The spectra of pressures at points in and behind the bomb bay of a Canberra aircraft have been obtained for a range of flight conditions. The primary objective of the flight measurement programme was to acquire data for comparison with pressure spectra obtained on a Wind tunnel model. This report describes the flight programme, and presents the results obtained. Comparison with wind tunnel experiments shows reasonably good agreement on rms pressure levels and spectrum shapes.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1025.pdf


    1059. Measurements of pressure fluctuations and skin friction on the upper surface of a slender wing at lift (M = 0.8 to 2.0)

    K. J. Turner, D. Walker
    ARC/CP-985
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0985.pdf


    1060. Measurements of secondary flow in the boundary layers of a 180 degree channel

    V.C. Patel
    ARC/CP-1043
    August 1968

    Secondary flow measurements have been made within the turbulent boundary layers at two streamwise cross-sections of a 180 degree curved channel. The results indicate substantial three-dimensionality on all four walls of the channel. The secondary flows on the flat and convex surfaces are in accordance with those expected from considerations of the action of the centrifugal pressure gradients on the flat surfaces, while those on the concave surface appear to be dictated both by this effect as well as by the occurrence of longitudinal instability vortices. Some attempts have been made to reduce the cross-flows on the curved surfaces so that the influence of streamwise surface curvature on nominally two-dimensional turbulent boundary layers can be investigated.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1043.pdf


    1061. Measurements of the effects of thickness on vortex breakdown position on a series of sharp-edged delta wings

    P. B. Earnshaw
    ARC/CP-1018
    February 1968

    Measurements have been made of vortex breakdown position on a series of symmetrical delta wings of 70 degrees sweep angle but differing thickness distribution using a schlieren system to detect the breakdown. The results demonstrate that the angles of incidence necessary to achieve a given position of breakdown over the wing can differ by at least as much as 5 degrees from a thin wing to a wing of 8% thickness-chord ratio. The tests also show the breakdown position to have a weak dependence on Reynolds number.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1018.pdf


    1062. Methods of solving the flutter equations in use at R.A.E

    T. Niblett
    ARC/CP-1046
    February 1968

    Details are given of some of the methods of solving the flutter equations which have been programmed in Mercury Autocode at the R.A.E. Included is a method of following the variation of critical speed with a linear variation of the structural inertia, damping or stiffness.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1046.pdf


    1063. Numerical solutions of hypersonic near-wake flow by the particle-in cell method

    R. I. Crane
    ARC/CP-1083
    August 1968

    Theoretical solutions of near wake flow have been obtained by application of the particle-in-cell numerical teohnique to hypersonic flow over the base of a cylindrical afterbody. Using the invisoid equations of motion and a uniform upstream flow, the flow angle after separation was found to be much smaller than experimental slender-body results suggested. However, the inclusion of a vortical layer representative of a boundary layer on the body resulted in a realistic wake flow pattern, although the lack of true viscosity was apparent in the profiles of flow properties. It is concluded that satisfactory near wake solutions by this method might be obtained by the use of realistic viscosity terms throughout the flow field and of a much finer representation of the approaching boundary layer, but the required computing power would be presently impracticable.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1083.pdf


    1064. On the driver-reservoir technique Part 1 Application to shock and gun tunnels Part 2 Determination of optimum reservoir size

    L. Davies, K. Dolman, D. R. Brown and G. Hooper
    ARC/CP-1019
    January 1968

    The driver-reservoir technique, first proposed by Henshall et al, is of interest to shock tunnel users because of its promise of an increase in running time. The most usual form of termination of running time in the shock tunnel is by the arrival, at the end plate, of the head of the rarefaction wave which results from the rupture of the main diaphragm. In the driver-reservoir technique, the head of the rarefaction wave interacts with a perforated plate, at the end of the high pressure chamber, which separates this chamber from a larger diameter vessel called the reservoir. Under certain conditions this results in no waves propagating downstream except Mach waves. The head of the expansion wave has therefore been effectively eliminated and this will result in an increase in running time. In this paper an account of the driver-reservoir technique is given, together with various theoretical analyses. A simple model is proposed which describes the wave processes within the reservoir, and the increase in running time to be expected from various Sizes of reservoir. From this model it is shown that the most important reservoir dimension is the diameter. Experiments from the NPL 2 in. shock tunnel are presented, and the application of the technique to gun tunnels is discussed.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1019.pdf


    1065. On the equilibrium piston technique in gun tunnels

    L. Davies, J.D. Regan and K.A. Dolman
    ARC/CP-982
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0982.pdf


    1066. On the prediction of laminarisation

    B. E. Launder and W. P. Jones
    ARC/CP-1036
    February 1968

    In rapid accelerations it is known that an originally turbulent boundary layer may undergo a partial or complete decay to laminar; a phenomenon known as laminarisation, The report distinguishes between 'moderate and 'severe' accelerations. For the former, the sublayer of the boundary layer undergoes considerable change in structure but the boundary layer remains essentially turbulent. For the latter, a complete degeneration to laminar flow will take place if the acceleration continues over sufficient distance. Two simple models have been proposed for the variation of turbulent shear stress, according to whether the acceleration is 'moderate' or 'severe'. These models have been incorporated into the finite difference prediction procedure of Patankar and Spalding and comparison made with a limited number of experiments. Agreement with experiment is reasonably good and progress to date has heen sufficiently encouraging to suggest that the accurate prediction of laminarisation is now an attainable objective.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1036.pdf


    1067. Optimum fibre arrangements for reinforced sheets under combined loading

    G. Z. Harris
    ARC/CP-975
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0975.pdf


    1068. Performance estimates for a reflected-shock tunnel with a modified driver to produce high test-section Reynolds numbers

    J. G. Woodley
    ARC/CP-1057
    November 1968

    Some calculations based on the performance of an ideal shock-tube are presented. These demonstrate the possibility of achieving a high test-section Reynolds number in a reflected-shock tunnel, employing nitrogen or air as the test gas, by the use of a driver gas composed of a mixture of hydrogen and nitrogen.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1057.pdf


    1069. Solution of the catapult take-off performance equations by an analogue method

    E. W. Addicott, R. W. Jones
    ARC/CP-977
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0977.pdf


    1070. The calculation of sub-critical pressure distributions on symmetric aerofoils at zero incidence

    P. G. Wilby
    ARC/CP-993
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0993.pdf


    1071. The correlation and prediction of pressure distributions on compression surfaces of sharp-edged conical bodies at high supersonic speeds

    M. J. Larcombe
    ARC/CP-1072
    May 1968

    A method for calculating the pressure distributions around conical bodies at high supersonic speeds, based on a local cone-flow theory, has been developed from the successful correlation of pressures at a symmetrical ridge line. The method is shown to provide a means for the accurate estimation of pressures on compression surfaces of conical bodies with sharp leading edges, providing the shock wave is detached from the edge.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1072.pdf


    1072. The development of a dummy bird for use in bird strike research

    A. W. R. Allcock and D. M. Collin
    ARC/CP-1071
    June 1968

    The problems of using bird carcases in bird strike testing are mentioned and the development of a dummy bird is described. Dummies of wax, wood, flexalkyd foam, emulsion and gelatine were tested, first by impacts on very simple basic target shapes, and then on engine inlet guide vane assemblies. Comparison of the results with those from chicken carcases showed that the foam, emulsion and gelatine dummies were all realistic simulators. The gelatine dummy is recommended because of its successful history of use as a flesh simulator in other types of impact study and because of its cheapness and ease of manufacture. The deflections measured using the special targets agreed quite well with simple theoretical calculations, and approximate values of the friction coefficient of the carcases and dummies were derived from high-speed films and the deflection measurements. The tests on the inlet guide vanes showed that blade damage was approximately proportional to projectile momentum, and that rotation of the (variable) blades even 5° out of the projectile line of flight greatly reduced their damage resistance.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1071.pdf


    1073. The dynamic stability derivatives of a slender wing, a comparison of theory with free-flight model tests at near-zero lift, M = 0.8 to 2.4

    K. J. Turner, A. Jean Ross, Geraldine Earley
    ARC/CP-995
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0995.pdf


    1074. The effect at M = 1.7 of removing swept endwalls from a wedge compression intake

    M. M. Shaw
    ARC/CP-1026
    March 1968

    Mean pressure recovery, distortion and the extent of stable subcritical flow have been measured at zero incidence on a fuselage side intake having a wedge compression surface. The intake was separated from the fuselage by a boundary layer diverter, and had a bleed on the compression surface just inside the entry plane. It was tested with and without bleed having top and bottom swept endwalls on, top endwalls on, and both endwalls off. Detailed measurements of duct total pressure were made at 1.8 times the capture height downstream of the inlet plane for all configurations. Removal of the endwalls leads to an increase in the uniformity of pressure distribution and to an increase in the range of stable subcritical flow.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1026.pdf


    1075. The effect of initial conditions on the development of turbulent boundary layers

    P. Bradshaw and D. H. Ferriss
    ARC/CP-986
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0986.pdf


    1076. The influence of gas streams and magnetic fields on electric discharges part 4 arcs moving along straight parallel electrodes

    V. W. Adams
    ARC/CP-987
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0987.pdf


    1077. The influence of gas streams and magnetic fields on electric discharges part 5 arcs at pressures up to 18 atmospheres in annular gaps

    V. W. Adams
    ARC/CP-988
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0988.pdf


    1078. The local pressure field of turbulent jets

    P. O. A. L. Davies, N. W. M. Ko and B. Bose
    ARC/CP-989
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0989.pdf


    1079. The new system for controlling the attitude and motivator deflections of a model in the R.A.E. no. 19 wind tunnel

    B. E. Pecover
    ARC/CP-1004
    January 1968

    A new closed loop system is described which enables the incidence, roll and motivator (i.e. control surface) angles of a wind tunnel model to be controlled remotely, either by hand or by analogue voltages derived from, say, a computer. Besides operating from direct (polar) demands, the system correctly positions the model if the demands are referred to Cartesian coordinates, and in this case compensation for sting bending can be made automatically. The system is described in some detail and the results of dynamic performance measurements are given.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1004.pdf


    1080. The pressure distribution at zero-lift on a slender delta wing at transonic speeds

    M. C. P. Firmin
    ARC/CP-991
    1968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0991.pdf


    1081. The stability of boundary conditions in the numerical solution of the time-dependent Navier-Stokes equations

    P. J. Taylor
    ARC/CP-1066
    August 1968

    This paper investigates the stability of finite-difference schemes, including boundary conditions, for solving the time-dependent Navier-Stokes equations. The different types of boundary condition whioh may occur are listed and no-slip conditions are derived for a wall with suction. Stability analyses are completed for one-dimensional problems with various types of boundary conditions, using schemes suitable for two-dimensional problems. All the conditions introduced are shown to be stable if there is no flow across the boundary. For suction at a fixed or moving wall, it is shown that the mesh size must be restricted for both accuracy and stability.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1066.pdf


    1082. The use of calibrated strain gauges for flight load determination

    P. B. Hovell, D. A. Webber, T. A. Roberts
    ARC/CP-1041
    July 1968

    An American statistical technique was evolved for the measurement of flight loads, but is of restricted use when applied to low aspect ratio multispar structures. This Report describes a modification in which a mixture of distributed loads (assembled by superposition of individual loads) and individual loads together with their corresponding strain gauge responses is used as a regression sample. This method is demonstrated on test results from a flight programme to measure fin loads on a Lightning aircraft.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1041.pdf


    1083. Wall corrections to longitudinal components measured on wind-tunnel models with tails

    D. A. Lovell
    ARC/CP-1075
    August 1968

    Calculations have been made of the magnitude of the wall corrections to pitching moment for two models with tails using two methods of correction and two stages of approximation for each method. It is found that the first stage of approximation is accurate enough for values of lift coefficient up to four. For higher values of lift coefficient, it is suggested that it is not worth using the second approximations as the theory of wind tunnel wall-interference is not sufficiently accurate in its predictions for flows with the large values of downwash inherent in high-lift systems such as lifting jets or rotors. The correction to lift calculated for the two models is shown to be nonnegligible and it is recommended that it is applied in tests where differences are to be taken between tail-on and tail-off tests.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1075.pdf


    1084. Wind tunnel investigation of jet interference for underwing installation of high bypass ratioengines

    D. J. Raney, A. G. Kurn, J. A. Bagley
    ARC/CP-1044
    March 1968

    Current design proposals for many swept-winged aircraft have large engines of high bypass ratio wih short fan cowls on short pylons under the wing, with the annular fan nozzle close to the wing leading edge. With such an arrangement there may be significant changes in the wing pressure distribution induced by the jet flow, particularly that from the fan. In consequence, the normal method of simulating the engine flow in a wind tunnel model, by using simple open ducts, and no representation of the jet thrust, might not be adequate. The tests reported here were planned as an initial investigation of jet interference for this type of configuration. Results show that for conventional locations of the nacelle on the wing, representation of the cruising jet thrust has only a small effect upon the wing pressure distribution and then only on the lower surface.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1044.pdf


    1085. A method of correlating the ground effects on the longitudinal characteristics of slender wings

    D. L. I. Kirkpatrick
    ARC/CP-1095
    September 1969

    This Report describes a method of calculating the ground effect on the longitudinal characteristics of a slender wing when the span/height ratio is small. The results obtained are compared with those obtained from Gersten's method, valid when the span/height ratio is large. From these two sets of results is derived a method of correlating the measured ground effects on the normal force and pitching moment on various slender wings, and hence a means of estimating the ground effect on any slender wing at any height above the ground.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1095.pdf


    1086. A preliminary experiment in resonance testing a rotating blade

    C. W. Skingle, D. R. Gaukroger, G. A. Taylor
    ARC/CP-1070
    April 1969

    An experiment to excite the flapping modes of a two-blade nonarticulated model rotor is described. The experiment was designed to develop a method of exciting a blade whilst it is rotating, and to measure the change of natural frequencies due to centrifugal effects. Three of the first four modes of the blade were excited over a range of rotational speeds, and the variations of frequency and damping with rotational speed are given for each mode.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1070.pdf


    1087. An investigation of the scatter in constant amplitude fatigue test results of aluminium alloys 2024 and 7075

    A. M. Stagg
    ARC/CP-1093
    April 1969

    A brief review of some of the investigations that have been conducted in the past into the form of the distribution of constant amplitude fatigue test results is presented and is followed by an analysis of a large amount of constant amplitude data for 2024 and 7075 materials collected from a variety of sources. This analysis, in terms of a log-normal distribution of life, confirms that the amount of scatter obtained in fatigue results increases with a decrease in the alternating stress amplitude. Further, a comparison of the scatter for the two materials is made and the effects on the scatter of such parameters as notch acuity and mean stress are investigated. The discussion is in terms of a simplified model of the fatigue mechanism and indicates a possible correlation between the amount of scatter and the number of crack nuclei present in a specimen.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1093.pdf


    1088. Civil aircraft airworthiness data recording programme some characteristics of severe turbulence

    G. E. King
    ARC/CP-1098
    July 1969

    The characteristics of severe turbulence suggested by an initial study of continuous trace records have been tested by examining turbulence encountered over a larger number of flying hours. Records from 23034 flying hours have been searched for patches of severe turbulence and those which produced the highest acceleration increments on the aircraft are presented in detail. It is found that the largest acceleration increment in a patch is on average 1.3 times the value that would be predicted from a Rayleigh distribution of peaks. About a half of the patches occurred without warning, and examination of outside air temperature data suggests that little additional warning would be provided by a conventional ram air temperature measuring device.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1098.pdf


    1089. Civil aircraft airworthiness data recording programme special events related to airspeed control practices (February 1963 to February 1966)

    CAADRP special events working party
    ARC/CP-1088
    June 1969

    Since October 1962 continuous trace records of airworthiness data have been taken from a small number of aircraft in normal airline service. Throughout the recording period the records have been searched for unusual occurrences, and each of these has been studied to determine its nature and, where possible, it's cause. This Report describes a selection of events related to airspeed control practices which were detected in records taken between February 1963 and February 1966, and a study of exceedences of airspeed limitations. CAADRP is a project administered by the Royal Aircraft Establishment in collaboration with the Air Registration Road, and involving a number of Airlines and Computer Instrumentation Limited.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1088.pdf


    1090. Civil aircraft airworthiness data-recording programme. Special events relating to handling and control (January 1963 to February 1966)

    CAADRP special events working party
    ARC/CP-1080
    February 1969

    Since October 1962 continuous trace records of airworthiness data have been taken from a small number of aircraft in normal airline service. Throughout the recording period the records have been searched for unusual occurrences, and each of these has been studied to determine its nature and, where possible, its cause. This Report describes a selection of Events relating to handling and control which were detected in records taken between January 1963 and February 1966. CAADRP is project administered by the Royal Aircraft Establishment in collaboration with the Air Registration Board, and involving a number of Airlines and C.I. Data Centre Limited.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1080.pdf


    1091. Cumulative fatigue damage studies of pinned-lug and clamped-lug structural elements in aluminium alloy

    W. T. Kirkby and P. R. Edwards
    ARC/CP-1089
    August 1969

    In this paper the results of cumulative fatigue damage studies are given for pinned-lug and clamped-lug specimens in aluminium alloys. The growth of fatigue damage under constant amplitude loading and under variable amplitude loading is discussed and the effects of static pre-load on subsequent fatiguen performance are illustrated. Explanations of the observed patterns of behaviour are put forward based on consideration of the residual stresses which may be induced by plastic defamation at stress concentrations within the test specimens. It is concluded that, in the present state of knowledge, it is advisable to use variable amplitude loading for component evaluation. The importance of using specimens having engineering configurations when evaluating new materials is also stressed.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1089.pdf


    1092. Gusts, discrete and indiscrete

    N. I. Bullen
    ARC/CP-1079
    March 1969

    For the analysis of gust loads on aircraft, a method is described in which the occurrence and magnitude of the loads are represented as random variables. The paper begins with the discrete gust, and goes on to treat the case in which the disturbances are too frequent to be considered singly and become indiscrete. In the limit this leads to the usual results obtained from the spectral approach, but in the observational material examined this limit is not reached. The simple mathematical model developed here gives a consistent picture gf the properties of observed gust load frequency distributions.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1079.pdf


    1093. List of current papers published for the aeronautical research council (numbers 1001-1050)

    Aeronautical Research Council
    ARC/CP-1050
    1969

    This paper lists fifty titles which have been published in the CP Series of the Aeronautical Research Council.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1050.pdf


    1094. List of current papers published for the Aeronautical Research Council (numbers 951 - 1000)

    Aeronautical Research Council
    ARC/CP-1000
    1969

    This paper lists fifty titles which have been published in the CP Series of the Aeronautical Research Council.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1000.pdf


    1095. Low altitude turbulence measurements over land and sea during flights in a Canberra aircraft

    E. W. Wells
    ARC/CP-1081
    June 1969

    A number of flights have been made at low altitude over a route in the U.K. which included legs flown ever land, and ever the sea at three and fifteen miles from the coast. Counting accelerometer records have been analysed and the turbulence encountered on the three legs compared. A brief analysis is made of the effect of wind on the turbulence.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1081.pdf


    1096. Low-speed wind-tunnel measurements of the oscillatory lateral stability derivatives for a model of a slender aircraft (HP 115) including the effects of frequency parameter

    J. S. Thompson, R. A. Fail, J. V. Inglesby
    ARC/CP-1097
    February 1969

    Low-speed tunnel tests on a model of the HP 115 aircraft have provided a complete set of lateral derivatives for a range of frequency parameters. Over a range appropriate to full scale flight, the effects of frequency parameter are small, but for very high values there is a marked reduction in the derivatives ... Some information is included on the derivatives ... and there is evidence that the virtual inertias are about the same wind-on and wind-off. The Paper also describes some recent improvements in technique.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1097.pdf


    1097. Modification of a normal shock by electrostatic forces

    G. F. Butler
    ARC/CP-1058
    March 1969

    The suggestion that the sonic bang may be alleviated by electrostatic means is examined and several objections to the idea are put forward. At the same time, some theoretical aspects of supersonic electrogasdynamics are investigated and the results presented.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1058.pdf


    1098. Nonlinear structural dynamics problems in aeronautics

    A. Simpson
    ARC/CP-1048
    January 1969

    This paper is concerned with the classification of nonlinear vibration problems which occur in the field of aeronautics - excluding those problems which may be more suitably defined under the heading 'nonlinear problems in control engineering'. It comprises a short catalogue of practical problems, methods of solution and relevant sources of reference.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1048.pdf


    1099. Normal shock-wave tables for air, argon, carbon dioxide, carbon monoxide, hydrogen, nitrogen, nitrous oxide, and oxygen

    K. C. Lapworth
    ARC/CP-1101
    June 1969

    Equilibrium conditions behind the incident and reflected shock wave are evaluated using the method of Ref. 1. In this method the enthalpy of the gas is regarded as the sum of two parts: (i) the enthalpy evaluated for a gas consisting of rigid molecules having no internal excitation and (ii) a correction term to be added to (i), to take account of internal excitation.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1101.pdf


    1100. The airborne path during take-off for constant rate-of-pitch manoeuvres

    D. H. Perry
    ARC/CP-1042
    1969

    A method of estimating the airborne path during take-off is proposed, based on the assumption that the aircraft is rotated at a constant rate of pitch from the moment of lift-off to the point at which it attains a steady climb path. The justification for this assumption is discussed. A simplified analysis, using small perturbation equations of motion, has been developed for initial project studies. Examples of the method applied to a slender wing transport aircraft, and a lightly loaded STOL aircraft are given, and the factors affecting the value of rate of pitch used are discussed.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1042.pdf


    1101. The calculation of three-dimensional turbulent boundary layers Part 4 comparison of measurements with calculations on the rear of a swept wing

    N.A. Cumpsty and M.R. Head
    ARC/CP-1077
    March 1969

    A boundary layer development was measured on the rear of a wing swept at 61°. The measurements approximately followed an external streamline from the minimum pressure to the neighbourhood of the separation line. Unfortunately the flow was found to be surprisingly sensitive to traverse gear interference. Moreover, the constraint imposed by the wind tunnel walls was sufficient to throw grave doubts on the use of the assumption of constant spanwise velocity to compute the external flow behaviour from the measured pressure distribution. Comparison of the measurements with calculations using the method proposed by Cumpsty and Head showed the growth of streamwise momentum thickness, form parameter and crossflow to be seriously underestimated. However, only a small adjustment to the spanwise velocity outside the boundary layer over the rear of the wing was sufficient to bring the results into tolerable agreement. The necessity for such an adjustment to the spanwise velocity may be plausibly explained by the effect of tunnel constraints.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1077.pdf


    1102. The influence of elevator movement on the normal accelerations experienced by a transport aircraft in moderate turbulence

    D. J. Eckford
    ARC/CP-1060
    January 1969

    Some excerpts from a record of data obtained in an encounter with moderate turbulence during routine operations by a transport aircraft are analysed in order to assess the contribution to the cg normal accelerations from the elevator movement produced by the automatic control system. It is found that this contribution is quite small and does not have a consistent effect on the amplitudes of the accelerations. The influence of an autostabilizer on the response in turbulent conditions is discussed for an idealised situation. From the analytical and numerical results obtained it is seen that the effectiveness of an autostabiliser will usually be strongly frequency-dependent. However, it is suggested that for the case considered here an autostabiliser with a pitch-rate law could gave a useful reduction in the cg normal accelerations experienced in turbulence: the most suitable value of the gearing appears to be that which produces a value of about 0.7 for the relative damping of the aircraft's short-period longitudinal mode.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1060.pdf


    1103. A brief account of some unrecorded techniques for flow visualization in flight for locating (a) boundary layer transition at altitude, (b) shock-wave position

    W. E. Gray
    ARC/CP-1090
    1970

    Flow visualization techniques, which have been successfully used in flight tests, are described. One indicates boundary-layer transition on a wing with a "china clay" coating, that is wetted at high altitude with a liquid of suitable volatility emitted by another aircraft; the result is photographed at altitude. The second shows the shock-wave position by the differential rippling of a viscous oil coating on the wing; it also reveals laminar flow areas by unrippled oil, at the same time. It relies on direct sunlight but is not over-sensitive to the direction of this, within quite wide limits. Comparative shock-wave results are given using an earlier direct sun-shadowgraph method which requires precise sun alignment and has been little used.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1090.pdf


    1104. A compressive test specimen for unidirectional carbon fibre reinforced plastics

    P. D. Ewins
    ARC/CP-1132
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1132.pdf


    1105. A Discussion of some Jet - Lift V/STOL Aircraft Characteristics and their likely Effect on Operational Applications

    D. Lean
    ARC/CP-1082
    June 1966

    Some of the characteristics of jet-lift V/STOL aircraft are discussed in terms of their effect on the ability of these aircraft to operate from small, semi-prepared sites, without the usual airfield facilities, in both good and bad visibility. Accumulated experience from experimental operations with jet-lift aircraft has been used as a basis for a tentative extrapolation to situations and conditions not yet (in 1964) examined in flight.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1082.pdf


    1106. Airflow rate requirements in passenger aircraft

    E. A. Timby
    ARC/CP-1136
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1136.pdf


    1107. Algol programmes for the response analysis of linear systems with deterministic or random inputs

    L. J. Hazlewood, E. Huntley
    ARC/CP-1124
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1124.pdf


    1108. An investigation of the scatter in variable-amplitude fatigue-test results of 2024 and 7075 materials

    A. M. Stagg
    ARC/CP-1123
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1123.pdf


    1109. An investigation of the stresses in a wind tunnel corner section

    D. E. W. Stone, P. S. A. Baxter
    ARC/CP-1117
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1117.pdf


    1110. An outline guide to criteria for the limitation of urban noise

    D. W. Robinson
    ARC/CP-1112
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1112.pdf


    1111. Civil aircraft airworthiness data recording programme special events relating to airspeed control and handling (January 1968 to February 1969)

    The CAADRP Special Events Working Party
    ARC/CP-1135
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1135.pdf


    1112. Delta wings with longitudinal camber at low speed

    R. K. Nangia and G. J. Hancock
    ARC/CP-1129
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1129.pdf


    1113. Effects of suction on the interaction between shock wave and boundary layer at a compression corner

    L. H. Tanner and S. L. Gai
    ARC/CP-1087
    1970

    The report describes work carried out in a supersonic wind tunnel at a Mach number of 1.93 on the interaction produced by wedges of 8°, 12° and 16° angle. The wedges could be raised from the tunnel floor through distances comparable with the boundary layer thickness, and suction was applied at the resulting slot. The pressure distributions and boundary layer traverses show how the suction reduces and eventually eliminates the separation region, causing the flow to approach that of ideal fluid theory. Estimates of optimum suction quantity and bleed height are obtained.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1087.pdf


    1114. Experimental investigation of the effect of trailing-edge sweepback on the subsonic longitudinal characteristics of slender wings

    D. L. I. Kirkpatrick, A. G. Hepworth
    ARC/CP-1130
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1130.pdf


    1115. Flight tests to investigate the problems of steep approaches by stol aircraft

    C. O. O'Leary, N. V. Slatter
    ARC/CP-1138
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1138.pdf


    1116. Gust response measurements on a model aircraft

    R. Cansdale, H. Hall
    ARC/CP-1113
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1113.pdf


    1117. Influence of wing root shaping on the pressure distribution of swept-wing body configurations

    J. Bridgewater and K. H. Wilson
    ARC/CP-1109
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1109.pdf


    1118. Ingestion of Debris into Intakes by Vortex Action

    D. E. Glenny and N. G. T. E. Pyestock
    ARC/CP-1114
    December 1968

    The advent of the big high by-pass ratio engines with their inherently large inlet diameters has resulted in engine installations featuring lower ground clearances than hitherto. Under these oiroumstances the vortex formed beneath the intake during ground running can be an extremely potent means of lifting ground debris into the intake. This Report oonsiders the impulsive lifting of particles over which the vortex core passes both on a theoretical and an experimental basis. Scaling laws are derived to relate model and full-scale tests and experimental evidence is cited to demonstrate their validity. For a given inlet velocity the strength of the vortex, and thus the maximum size of particle that can be lifted, is very much a function of the ambient vorticity, and of the strength of the wind blowing on to the intake. The ability of atmospheric vorticity to vary from one instant to the next leads to some difficulty in specifying the maximum size of particle that the vortex might lift. Nevertheless it seems reasonable on the basis of the evidence submitted that a 6 ft diameter intake operating with the centreline 6 ft above the ground, as is representative of some current projects, would be capable of ingesting spherical pieces of concrete up to 12 in. in diameter. Various methods of reducing ingestion were examined experimentally, and although some undoubtedly decreased the frequency of ingestion none provided an absolute safeguard. However, an operational technique which might ease the ingestion problem involves a progressive throttle opening as the aircraft initially accelerates on take-off so as to achieve as high a value as possible for the ratio of the wind velocity blowing on to the intake to the intake throat velocity.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1114.pdf


    1119. Interference effects at M = 8.5 of wires and probes on the wake of a magnetically suspended rounded base cone

    J. F. W. Crane
    ARC/CP-1133
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1133.pdf


    1120. Interim note on tests with a wing mounted fan nacelle with the fan jet simulated by cold air blowing and alternatively by a gas generator shroud

    G. Pauley
    ARC/CP-1111
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1111.pdf


    1121. Liquid and vapour cooling systems for gas turbines

    J P Edwards
    ARC/CP-1127
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1127.pdf


    1122. Low speed flight tests on a tailless delta wing aircraft (Avro 707B) part 3 lateral stability and control

    D. H. Perry, J. C. Morrall, W. G. A. Port
    ARC/CP-1106
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1106.pdf


    1123. Low speed flight tests on a tailless delta wing aircraft (Avro 707B) part 4 wing flow

    D. H. Perry, W. G. A. Port, J. C. Morrall
    ARC/CP-1107
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1107.pdf


    1124. Low-speed characteristics of waverider wings

    R. F. A. Keating, B. L. Mayne
    ARC/CP-1118
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1118.pdf


    1125. Low-speed wind-tunnel tests on an unswept wing-fuselage model of aspect ratio 9.8, with tangential blowing over trailing-edge flaps and ailerons, including the effect of slipstream

    J. A. Lawford
    ARC/CP-1108
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1108.pdf


    1126. Non-equilibrium emissivity of carbon dioxide near 4.3 mu

    J.P. Hodgson
    ARC/CP-1116
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1116.pdf


    1127. Operational and theoretical studies on the effect of pilot action on heavy landings

    H. Hall, G. B. Hutton
    ARC/CP-1119
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1119.pdf


    1128. Results and analysis of pressure measurements on two isolated slender wings and slender wing-body combinations at supersonic speeds part 1 analysis

    K. A. Fellows and E. C. Carter
    ARC/CP-1131
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1131.pdf


    1129. Some flight and wind-tunnel longitudinal stability measurements on the bac 221 slender-wing aircraft

    C. S. Barnes, R. Rose
    ARC/CP-1134
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1134.pdf


    1130. Some observations on the heat transfer characteristics of a rotating mixed convection thermosyphon

    W. D. Morris
    ARC/CP-1115
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1115.pdf


    1131. Super VC 10 cruise drag - a wind tunnel investigation part 1 experimental techniques

    C. R. Taylor, J. R. Hall, R. W. Hayward
    ARC/CP-1125
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1125.pdf


    1132. Temperature and fluid property effects on cavitation in aircraft fuel pumps

    W. G. S. Lester
    ARC/CP-1128
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1128.pdf


    1133. Tests at a mach number of 2.0 on a rectangular, twin-duct air intake with variable geometry, situated in the flow field of a slender wing

    M. D. Dobson
    ARC/CP-1122
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1122.pdf


    1134. The estimation of the loading on swept wings with extending chord flaps at subsonic speeds

    J. McKie
    ARC/CP-1110
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1110.pdf


    1135. The role of heat conduction in leading edge heating theory and experiment

    T. Nonweiler, H. Y. Wong, S. R. Aggarwal
    ARC/CP-1126
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1126.pdf


    1136. The use of cross-correlation and power spectral techniques for the identification of the hunter MK.12 dynamic response

    D. E. Fry
    ARC/CP-1121
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1121.pdf


    1137. Vertical acceleration in the cockpit of a subsonic transport aircraft during take-off measured during airline operation

    C. G. B. Mitchell
    ARC/CP-1120
    1970

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1120.pdf


    1138. A feasibility study on a 200 volt, direct current, aircraft electrical power system

    The Staff of the Auxiliary Power Systems Division of Engineering Physics Department
    ARC/CP-1186
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1186.pdf


    1139. A further wind tunnel investigation of underwing jet interference

    A. G. Kurn
    ARC/CP-1156
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1156.pdf


    1140. A novel method for the estimation of the zero-lift forebody pressure drag of axisymmetric non-slender shapes at supersonic and hypersonic velocities

    P. G. Pugh and L. C. Ward
    ARC/CP-1142
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1142.pdf


    1141. A numerical procedure for constructing shock-wave envelopes around conical bodies using data from Schlieren photographs

    M. J. Larcombe
    ARC/CP-1143
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1143.pdf


    1142. A parallel motion creep extensometer

    J. N. Webb
    ARC/CP-1173
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1173.pdf


    1143. A systematic approach to the design of radial inflow and mixed flow turbines

    F. J. Wallace
    ARC/CP-1180
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1180.pdf


    1144. Air condensation effects at M = 8.5 measured on the drag and the wake of a magnetically suspended 20 deg. cone

    J. F. W. Crane
    ARC/CP-1177
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1177.pdf


    1145. An experimental investigation of supersonic boundary-layer flows with pressure gradients

    S. Sivasegaram
    ARC/CP-1190
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1190.pdf


    1146. An hypothesis for the prediction of flight penetration of wing buffeting from dynamic tests on wind tunnel models

    D. G. Mabey
    ARC/CP-1171
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1171.pdf


    1147. An improved technique of stability testing in free flight at transonic speeds, applied to a non-lifting slender wing

    A. P. Waterfall
    ARC/CP-1174
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1174.pdf


    1148. An investigation of the pressure distributions on a 45 degree swept half wing including the effects of upper surface spoilers

    M. D. Dobson
    ARC/CP-1184
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1184.pdf


    1149. Boundary-Layer Prediction Methods Applied to Cooling Problems in the Gas Turbine

    F. J. Bayley, W. D. Morris, J. M .Owen and A. B. Turner,
    ARC/CP-1164
    May, 1970

    In this paper data obtained in a range of experimental investigations of cooling problems in the gas turbine are compared with theoretical predictions made by using a number of hypotheses concerning the analysis of turbulent boundary layers. Integral and differential theories have been used, and applied to flows over convection- and transpiration-cooled turbine blades and simplified representations of combustion systems and turbine discs. *Replaces A.R.C.32 050

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1164.pdf


    1150. Brief flight tests of crosswind landings and sidestep manoeuvres on the BAC 221 aircraft

    F. W. Dee, R. Rose and O. P. Nicholas
    ARC/CP-1168
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1168.pdf


    1151. Civil aircraft airworthiness data recording programme achievements in recording and analysis of civil aircraft operations 1962-1969

    E. Marjorie Owen
    ARC/CP-1181
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1181.pdf


    1152. Civil aircraft airworthiness data recording programme hard landings encountered by subsonic civil jet aircraft

    The CAADRP special events working party
    ARC/CP-1182
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1182.pdf


    1153. Civil aircraft airworthiness data recording programme manoeuvre loads during training and test flying

    G. E. King
    ARC/CP-1176
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1176.pdf


    1154. Civil aircraft airworthiness data recording programme special events of meteorological origin (January 1966 to November 1968)

    The CAADRP special events working party
    ARC/CP-1188
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1188.pdf


    1155. Cumulative damage in fatigue with particular reference to the effects of residual stresses

    P. R. Edwards
    ARC/CP-1185
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1185.pdf


    1156. Curvature effects in the diffraction of short waves into a shadow

    F. G. Leppington
    ARC/CP-1193
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1193.pdf


    1157. Experimental investigation of a high-lift low-drag aerofoil

    F. H. Kelling
    ARC/CP-1187
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1187.pdf


    1158. Experimental verification of predicted static hole size effects on a model with large streamwise pressure gradients

    P. G. Pugh, J. W. Peto and L. C. Ward
    ARC/CP-1139
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1139.pdf


    1159. Flight and wind-tunnel tests on an aerodynamically compensated pitot-static head for the BAC 221 aircraft

    C. S. Barnes and O. P. Nicholas
    ARC/CP-1167
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1167.pdf


    1160. Flow unsteadiness and model vibration in wind tunnels at subsonic and transonic speeds

    D. G. Mabey
    ARC/CP-1155
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1155.pdf


    1161. Gun tunnel force measurements on some thin delta wings suitable for hypersonic cruising flight

    T. Opatowski
    ARC/CP-1148
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1148.pdf


    1162. Induced rolling moment characteristics of the M557A streamline bomb at mach number 0.50

    P. Lee, I. G. Hacker
    ARC/CP-1157
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1157.pdf


    1163. Low-speed wind-tunnel calibrations of the pitot and static pressure sensors and wind vanes on the short SC 1 aircraft

    K. P. King, E. N. Rowthorn
    ARC/CP-1162
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1162.pdf


    1164. Low-speed wind-tunnel measurements of surface pressure fluctuations on two slender-wing models

    D. A. Lovell, T. B. Owen
    ARC/CP-1154
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1154.pdf


    1165. Low-speed wind-tunnel tests on a family of cambered wings of mild gothic planform of aspect ratio 1.4

    P. J. Butterworth
    ARC/CP-1163
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1163.pdf


    1166. Notes on the diffraction of sound

    J. C. Cooke
    ARC/CP-1192
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1192.pdf


    1167. On large and rapid wind fluctuations which occur when the wind had previously been relatively light

    J. Burnham, M. J. Colmer
    ARC/CP-1158
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1158.pdf


    1168. On the spontaneous ignition temperature of organic materials in oxygen

    Hilda C. Attwood and G. R. Allen
    ARC/CP-1172
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1172.pdf


    1169. Parameter estimation for the log-normal parent population of fatigue failures from a sample containing both failed and non-failed members

    A. M. Stagg
    ARC/CP-1144
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1144.pdf


    1170. Piloted simulator investigations of flight near zero rate of climb speed

    T. Wilcock
    ARC/CP-1165
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1165.pdf


    1171. Pitot-stem blockage corrections in uniform and non-uniform flow

    R. W. F. Gould
    ARC/CP-1175
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1175.pdf


    1172. Pressures near the centre-line of Leeward surfaces on delta wings and conical bodies at high supersonic speeds

    M. J. Larcombe
    ARC/CP-1153
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1153.pdf


    1173. Progress Report on Observations of Three-Dimensional Flow Patterns obtained during Stall Development on Aerofoils, and on the Problem of Measuring Two-Dimensional Characteristics

    N. Gregory, V. G. Quincey, C L O'Reilly and D. J. Hall
    ARC/CP-1146
    January 1970

    Surface oil-flow patterns were used at low speeds on both thick and thin aerofoils to show the onset of three-dimensionality in either separation or re-attachment when there is an appreciable extent of the separated flow that accompanies the development of the stall. Observations on a thick aerofoil in compressible flow showed a similar trend in the re-attachment behind a shock-induced separation. A form of boundary layer control applied at the corners at the ends of the aerofoil was able to prevent separation of the corner flow but not to inhibit the development of three-dimensionality.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1146.pdf


    1174. Results of a series of flights in the stratosphere over mountainous terrain in the Western U.S.A. during February, 1967

    A. McPherson, J. M. Nicholls
    ARC/CP-1159
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1159.pdf


    1175. Results of a series of wind tunnel model breakdown tests on the trident 1 aircraft and a comparison with drag estimates and full scale flight data

    J. I. Simper, P. G. Hutton
    ARC/CP-1170
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1170.pdf


    1176. Scale effects on oscillatory control-surface derivatives

    A. W. Moore
    ARC/CP-1151
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1151.pdf


    1177. Some full-scale measurements of the flow in the wake of a hangar

    M. J. Colmer
    ARC/CP-1166
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1166.pdf


    1178. Some mechanical properties of DTD 5025 magnesium alloy castings

    R. T. Potter
    ARC/CP-1160
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1160.pdf


    1179. Some observations on vortex shedding and acoustic resonances

    M. Gaster
    ARC/CP-1141
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1141.pdf


    1180. Subsonic theoretical lift-curve slope, aerodynamic centre and spanwise loading for arbitrary aspect ratio, taper ratio and sweepback

    H. C. Garner and Sandra M. Inch
    ARC/CP-1137
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1137.pdf


    1181. The aerodynamic effect of ground proximity on lateral control of slender aircraft in the landing approach

    W. J. G. Pinsker
    ARC/CP-1152
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1152.pdf


    1182. The drift of an auto-pilot gyroscope due to prolonged acceleration in the skylark rocket abridged version

    F. R. Knott
    ARC/CP-1147
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1147.pdf


    1183. The effect of small conical thickness distributions on the separated flow past slender delta wings

    H. Portnoy and S. C. Russell
    ARC/CP-1189
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1189.pdf


    1184. The performance of two axial-flow compressors of differing blade aspect ratio

    G .J. S. Fahmi
    ARC/CP-1179
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1179.pdf


    1185. Theoretical assessment of a method for the flight measurement of net engine thrust using towed drag devices

    W. J. Pinsker
    ARC/CP-1169
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1169.pdf


    1186. Theoretical pressure distributions on four simple wing shapes for a range of supersonic flow conditions

    J. Pike
    ARC/CP-1178
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1178.pdf


    1187. Two dimensional low-speed tunnel tests on the N.A.C.A. 0012 section including measurements made during pitching oscillations at the stall

    G. F. Moss, P. M. Murdin
    ARC/CP-1145
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1145.pdf


    1188. Vertical cockpit accelerations measured on an operational jet transport aircraft

    G. B. Hutton
    ARC/CP-1183
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1183.pdf


    1189. Vibration levels experienced in take-off on a large flexible aircraft

    H. Hall
    ARC/CP-1149
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1149.pdf


    1190. Vibrational equilibrium calculations of properties behind reflected shock waves with tables for CO2 and N2O

    R. J. Hine
    ARC/CP-1201
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1201.pdf


    1191. Wind tunnel measurements at M = 2.47 of the mutual aerodynamic interference between a guided bomb and its boost unit during the separation phase

    J. A. Lang
    ARC/CP-1161
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1161.pdf


    1192. Wind tunnel tests at transonic and supersonic speeds to investigate the longitudinal stability of a model of the avro 720 aircraft

    E. Huntley
    ARC/CP-1140
    1971

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1140.pdf


    1193. A comparison between two methods of analysis of oscillatory pressure measurements, one method requiring the use of a tape recorder

    A. W. Moore, B. L. Welsh
    ARC/CP-1205
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1205.pdf


    1194. A comparison of the surface-source solution with an exact solution for the twodimensional inviscid flow about a slotted-flap aerofoil

    B. R. Williams
    ARC/CP-1214
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1214.pdf


    1195. A computer program to calculate the pressure distribution on an annular aerofoil

    C. Young
    ARC/CP-1217
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1217.pdf


    1196. A laboratory comparison of three methods of personal conditioning

    J.R. Allan et al
    ARC/CP-1210
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1210.pdf


    1197. A method of improving aircraft ground performance in slush and wet conditions

    R. V. Barrett
    ARC/CP-1206
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1206.pdf


    1198. A result concerning the supersonic flow below a plane delta wing

    P. L. Roe
    ARC/CP-1228
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1228.pdf


    1199. A review of some published data on the external-flow jet-augmented flap

    D. H. Perry
    ARC/CP-1194
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1194.pdf


    1200. A review of wind tunnel tests on circulation-control devices for aircraft control

    F. G. Maccabee, B. R. Hilton and J. I. Marsh
    ARC/CP-1232
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1232.pdf


    1201. A simulator study of direct lift control

    A. G. Barnes, D. E. A. Houghton and C. Colclough
    ARC/CP-1199
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1199.pdf


    1202. A theoretical investigation of supersonic jets in subsonic flow fields

    C. Young
    ARC/CP-1256
    September 1972

    A method of calculating the development of a supersonic jet exhausting into a subsonic free stream is presented. The method of characteristics is used with the conditions on the jet boundary modified by the change in static pressure produced by the external stream. The method is particularly applied to cases where the inner boundary of the jet is a solid surface, e.g. the fan exhaust of a bypass engine. Theory and experiment are in close agreement for the range of jet pressure ratios and free-stream Mach numbers associated with engines of high bypass ratio.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1256.pdf


    1203. Aerodynamic data for the BAC 221 up to a mach number of 0.955 as measured in wind tunnel tests

    Dorothy M. Holford
    ARC/CP-1230
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1230.pdf


    1204. An examination of an iterative procedure for determining the characteristic exponents of linear differential equations with periodic coefficients

    D. L. Woodcock, D. Elton and R. J. Davies
    ARC/CP-1218
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1218.pdf


    1205. An investigation of transition fixing technique for a 10.5% thick, 28 degrees sweptback wing at high subsonic speeds and R is semilar to 3 x 106

    P. G. Hutton
    ARC/CP-1215
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1215.pdf


    1206. Andover C. Mk. 1 airfield criteria trials

    J. Howell
    ARC/CP-1220
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1220.pdf


    1207. Boundary-layer pressure fluctuations at high Reynolds numbers on a free-flight test vehicle

    D. R. Roberts
    ARC/CP-1208
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1208.pdf


    1208. Calculation of the annulus wall boundary layers in axial flow turbomachines

    J. H. Horlock and D. Hoadley
    ARC/CP-1196
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1196.pdf


    1209. Design development of an aircraft strut in carbon fibre reinforced plastic

    T. A. Collings
    ARC/CP-1229
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1229.pdf


    1210. Dynamic calibration of gas flowmeters

    K. R. Maslen
    ARC/CP-1224
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1224.pdf


    1211. Exploratory tests on a forward-mounted overwing engine installation

    D. J. Kettle, A. G. Kurn, J. A. Bagley
    ARC/CP-1207
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1207.pdf


    1212. Flow in a supersonic jet expanding from a convergent nozzle

    J. C. Gibbings, J. Ingham and D. Johnson
    ARC/CP-1197
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1197.pdf


    1213. Fortran Programmes for Axisymmetric Potential Flow Around Closed and Semi-Infinite Bodies

    C. M. Albone
    ARC/CP-1216
    March 1970

    Two programmes are presented in I.C.L. FORTRAN, for the pressure distribution on the surface of an arbitary body of revolution in axisymmetric, incompressible flow. One programme evaluates the pressure distribution on an arbitary closed body of revolutlon. The second deals with a body which has a parallel afterbody extending to infinity downstream. Listings for each programme are given in the Appendicies. Results from both programmes are presented and their accuracy is demonstrated. The range of bodies for which the programmes work is also shown. Replaces A.R.C.32,346

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1216.pdf


    1214. Fortran subroutines for finite element analysis

    B. C. Merrifield
    ARC/CP-1223
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1223.pdf


    1215. Heat transfer and surface pressure measurements on two conical wings in free flight up to M = 4.5

    G. H. Greenwood
    ARC/CP-1212
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1212.pdf


    1216. List of Current Papers Numbers 1151-1200


    ARC/CP-1200

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1200.pdf


    1217. List of Current Papers published for the Aeronautical Research Council. Nos. 1101-1150


    ARC/CP-1150

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1150.pdf


    1218. Low speed pull-up manoeuvres for a slender wing transport aircraft with stability and control augmentation

    Dorothy M. Holford
    ARC/CP-1231
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1231.pdf


    1219. Notes on the internal drag, lift and pitching moment of a ducted body

    J. W. Britton, M. D. Dobson
    ARC/CP-1211
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1211.pdf


    1220. Optimum engine thrust deflection for high-speed cruising aircraft

    J. Pike
    ARC/CP-1222
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1222.pdf


    1221. Papers on novel aerodynamic noise source mechanisms at low jet speeds

    John E. Ffowcs Williams et al
    ARC/CP-1195
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1195.pdf


    1222. Pressure Distributions at M = 3.51 and at High Incidences on Four Wings with Delta Planform

    R. Hilller
    ARC/CP-1198
    March 1971

    Results are presented for wind tunnel tests at M(infinity) = 3.51 on four wings with pointed vertices and sharp leadlng edges. Two conical models were tested through a wide range of angles of incidence and yaw and the results clearly demonstrate the stabilising effect of dihedral. Two simple non-conical wings were also tested and it 1s shown, in this case, that the pressure on the compression surfaces may be approximately deduced from an 'equivalent' conical wing.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1198.pdf


    1223. Some aerodynamic considerations of the flight characteristics of towing systems using long towlines at high speeds

    D. Pierce and L. J. Beecham
    ARC/CP-1235
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1235.pdf


    1224. Some experiences with "on-line" spectral analysis using a small digital computer

    J. B. Roberts and D. Surry and R. F. Johnson
    ARC/CP-1225
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1225.pdf


    1225. Some measurements of base pressure fluctuations at subsonic and supersonic speeds

    D. G. Mabey
    ARC/CP-1204
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1204.pdf


    1226. Some modifications to the calculation method for wings with part-span extending-chord flaps given in rae technical report 69034

    J. McKie
    ARC/CP-1213
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1213.pdf


    1227. Spontaneous ignition of avtur vapour in various oxygen-nitrogen mixtures

    J. T. Cansdale
    ARC/CP-1209
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1209.pdf


    1228. The design of high sensitivity pressure transducers for use in shock-tunnels

    R. O. Goodchild and L. Bernstein
    ARC/CP-1219
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1219.pdf


    1229. The dynamic behaviour of crash helmets

    J.M. Rayne
    ARC/CP-1202
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1202.pdf


    1230. The effect of an application of heat on the fatigue performance under random loading of a notched specimen of DTD 5014 (RR58) material

    J. R. Heath-Smith, Judy E. Aplin
    ARC/CP-1221
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1221.pdf


    1231. The longitudinal stability characteristics of an ogee wing of slenderness ratio = 0.35

    A. G. Hepworth
    ARC/CP-1227
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1227.pdf


    1232. The measurement and analysis of the profile drag of a wing with a slotted flap

    I. R. M. Moir, D. N. Foster and D. R. Holt
    ARC/CP-1233
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1233.pdf


    1233. The multiple quantum jump model for vibrational energy relaxation

    Michael J. Lewis and Leonard Bernstein
    ARC/CP-1191
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1191.pdf


    1234. The off-design analysis of flow in axial compressors

    H. Daneshyar and M. R. A. Shaalan
    ARC/CP-1234
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1234.pdf


    1235. The unsteady response of an axial flow compressor with a distorted inlet flow

    H. Mokelke
    ARC/CP-1203
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1203.pdf


    1236. Transonic fan noise

    D. Hawkings
    ARC/CP-1226
    1972

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1226.pdf


    1237. A study of the effect of the wake of the main aerofoil of a fowler-flap configuration on the lift of the flap

    P. R. Ashill
    ARC/CP-1257
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1257.pdf


    1238. A suggestion for improving flap effectiveness by heat addition

    J. Martin
    ARC/CP-1252
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1252.pdf


    1239. A technique for measuring oscillatory aerodynamic control surface hinge moments from forced response characteristics

    D. R. Gaukroger, D. A. Drane and R. Gray
    ARC/CP-1253
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1253.pdf


    1240. A theoretical investigation of supersonic jets in subsonic flow fields

    C. Young
    ARC/CP-1256
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1256.pdf


    1241. A two-dimensional mathematical model of a parachute in steady descent

    R. G. Hume
    ARC/CP-1260
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1260.pdf


    1242. Aerodynamic characteristics of NPL 9626 and NPL 9627, further aerofoils designed for helicopter rotor use

    P. G. Wilby, N. Gregory and V. G. Quincey
    ARC/CP-1262
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1262.pdf


    1243. Afterbody drag measurement at transonic speeds on a series of twin and single jet afterbodies terminating at the jet-exit

    O. M. Pozniak and A. B. Haines
    ARC/CP-1266
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1266.pdf


    1244. An omni-directional velocity vector probe suitable for use in gas turbine combustors design development and preliminary tests in a model combustor

    J. J. Macfarlane
    ARC/CP-1254
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1254.pdf


    1245. Comparative turbulence for a Canberra and a vulcan flying together at low altitude

    J. K. Curran
    ARC/CP-1244
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1244.pdf


    1246. Decay of trailing vortices

    E. H. Oon
    ARC/CP-1238
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1238.pdf


    1247. Gust loads on comet aircraft

    I. W. Kaynes
    ARC/CP-1247
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1247.pdf


    1248. List of current papers (numbers 1201-1250)

    Aeronautical Research Council
    ARC/CP-1250
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1250.pdf


    1249. Measurement of the Internal Performance of a Rectangular Air Intake having Variable Geometry Compression Surfaces at Mach Numbers from 1.7 to 2.5. Part 11 The Effect of Incidence

    C. S. Brown and E. L. Goldsmith
    ARC/CP-1242
    December 1971

    Measurements have been made of the internal performance of a rectangular intake having variable geometry compression surfaces. The measurements have been made within a range of Mach numbers from 1.7 to 2.46 and at angles of incidence up to 10°. The Reynolds number based on intake height was about 1.5 x 106 for Mach numbers above 2 and 0.6 x 106 for Mach numbers below 2. Some measurements at M=2.01 were made at both Reynolds numbers. The results confirm the findings of Part I of this Report that shock patterns can be used to predict accurately maximum mass flow and shock pressure recovery provided the assumption is made that the initial wedge angle is increased by just under one degree. The results also show that simple assumptions can be made as to the form of the shock pattern in order to extend these predictions into regions of shock detachment which arise inevitably when the intake is at large angles of incidence. A simple correlation of losses other than shock losses with a 'turning loss' factor used in Part I, is found to serve equally well when the intake operates over a range of incidence from 0° to 10°.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1242.pdf


    1250. Measurement of the internal performance of a rectangular air intake with variable geometry at mach numbers from 1.7 to 2.5 part 1

    C. S. Brown and E. L. Goldsmith
    ARC/CP-1243
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1243.pdf


    1251. Measurements of temperature and pressure behind the incident and reflected shocks in a shock tube

    Michael J. Lewis and Leonard Bernstein
    ARC/CP-1239
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1239.pdf


    1252. NPL 9615 and NACA 0012 a comparison of aerodynamic data

    N. Gregory and P. G. Wilby
    ARC/CP-1261
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1261.pdf


    1253. On the calibration of pressure transducers for use in shock-tunnels

    R. O. Goodchild and L. Bernstein
    ARC/CP-1240
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1240.pdf


    1254. On the effects of viscous interaction for a flat delta wing at incidence

    L. Davies
    ARC/CP-1237
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1237.pdf


    1255. On the influence of camber and non-planar vortex wake on wing characteristics in ground effect

    B. Maskew
    ARC/CP-1264
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1264.pdf


    1256. On the nature of large clear air gusts near storm tops

    Anne Burns
    ARC/CP-1248
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1248.pdf


    1257. Plane turbulent jet flow in a favourable pressure gradient

    M. J. Riley
    ARC/CP-1236
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1236.pdf


    1258. Similarity requirements for aeroelastic models of helicopter rotors

    G. K. Hunt
    ARC/CP-1245
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1245.pdf


    1259. Some examples of the application of methods for the prediction of boundary-layer transition on sheared wings

    D. A. Treadgold and J. A. Beasley
    ARC/CP-1246
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1246.pdf


    1260. The calculated growth of lift and moment on a swept wing entering a discrete vertical gust at subsonic speeds

    H. C. Garner
    ARC/CP-1241
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1241.pdf


    1261. The calculation of compressible turbulent boundary layers with fluid injection

    L. C. Squire and V. K. Verma
    ARC/CP-1265
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1265.pdf


    1262. The effect of leading-edge geometry on high-speed stalling

    G. F. Moss, A. B. Haines and R. Jordan
    ARC/CP-1251
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1251.pdf


    1263. Wind-tunnel force measurements on a .05 scale model of black arrow at mach numbers of 1.2, 1.5 and 2.0

    J. R. Hall
    ARC/CP-1249
    1973

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1249.pdf


    1264. A calculation method for the turbulent boundary layer on an infinite yawed wing in compressible, adiabatic flow

    P. D. Smith
    ARC/CP-1268
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1268.pdf


    1265. A calculation method for the two-dimensional turbulent flow over a slotted flap

    H. P. A. H. Irwin
    ARC/CP-1267
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1267.pdf


    1266. A comparison of flight loads counting methods and their effects on fatigue life estimates using data from concorde

    Ann G. Goodwillie
    ARC/CP-1304
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1304.pdf


    1267. A parametric study of the use of nose blunting to reduce the supersonic wave drag of forebodies

    P. G. Pugh and L. C. Ward
    ARC/CP-1271
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1271.pdf


    1268. A prediction method for pressure distributions on compression surfaces of conical bodies at supersonic speeds

    M. J. Larcombe
    ARC/CP-1295
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1295.pdf


    1269. A shock capturing method for calculating supersonic flow fields

    F. Walkden and P. Caine
    ARC/CP-1290
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1290.pdf


    1270. A two-dimensional aerofoil oscillating at low frequencies in high subsonic flow

    D. Nixon
    ARC/CP-1285
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1285.pdf


    1271. An aeroelastic model helicopter rotor

    R. Cansdale
    ARC/CP-1288
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1288.pdf


    1272. Application of a variational method in plane compressible flow calculation

    H. Rasmussen, N. Heys
    ARC/CP-1284
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1284.pdf


    1273. Asymmetric wing loads on a Canberra Aircraft during flight in turbulence

    J. P. Thompson
    ARC/CP-1270
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1270.pdf


    1274. Boundary-layer pressure fluctuations at high reynolds numbers on a second free-flight test vehicle

    D. R. Roberts
    ARC/CP-1302
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1302.pdf


    1275. Civil aircraft airworthiness data recording programme a study of normal operational landing performance on subsonic civil jet aircraft

    G. B. Hutton
    ARC/CP-1273
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1273.pdf


    1276. Civil aircraft airworthiness data recording programme uneven runways encountered by subsonic jet transport aircraft during scheduled airline operations

    G. B. Hutton
    ARC/CP-1287
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1287.pdf


    1277. Comparison between dynamic stability boundaries for NPL 9615 and NACA 0012 aerofoils pitching about the quarter-chord

    A. W. Moore, N. C. Lambourne, L. Woodgate
    ARC/CP-1279
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1279.pdf


    1278. Deformation and Failure under Multiaxial Stresses - A Survey of Laboratory Techniques and Experimental Data

    W.J. Evans
    ARC/CP-1306
    January 1972

    A survey has been made of techniques for producing multiaxial stress conditions on a laboratory scale and it is concluded that one of the more suitable systems is combined tension-torsion of thin-walled tubes. Experimentally this technique, although complex, appears to offer several advantages. Furthermore, the shear/normal stress ratio can be conveniently controlled, thus enabling deformation and fracture mechanisms under multiaxial stresses to be studied. A review has also been presented of relevant experimental work, most of which has been concerned with assessment of the various deformation and failure criteria. Although there is some correlation for yield data, ductile or brittle fracture and creep behaviour, the situation is not nearly so well defined for fatigue. Work on the micro-structural effects of biaxial stresses is also considered. It would appear that although the mechanisms by which dislocations operate remain unchanged from the uniaxial state, modifications can occur to the products of interactions between dislocations. In addition fracture behaviour can be altered by the ratio of tensile to shear stress. Generally, however, little work has been published on this aspect of deformation behaviour. It is concluded that it is important to study micro-structural effects particularly in relation to design criteria. *Replaces NGTE NT 833 - A.R.C.33753.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1306.pdf


    1279. Development of a model technique for investigating the performance of soft-ground arresters for aircraft

    J. R. Barnes
    ARC/CP-1275
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1275.pdf


    1280. Fatigue endurance, crack sensitivity and nucleation characteristics of structural elements in four aluminium-copper alloys

    F. E. Kiddle
    ARC/CP-1259
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1259.pdf


    1281. Fatigue tests on plain specimens of titanium 6A1-4V under variable amplitude loading

    A. W. Cardrick, B. H. E. Perrett
    ARC/CP-1276
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1276.pdf


    1282. Film cooling effectiveness from rows of holes under simulated gas turbine conditions

    M.R. Smith, T.V. Jones and D.L. Schultz
    ARC/CP-1303
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1303.pdf


    1283. Flight determination of the rudder power and directional stability of the fairey delta 2 aircraft using a wingtip parachute

    G. Ingle
    ARC/CP-1298
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1298.pdf


    1284. Flight Simulation of a Wessex Helicopter - A Validation Exercise

    T. Wilcock and Ann C. Thorpe
    ARC/CP-1299
    May 1973

    A piloted flight simulation of the Westland Wessex helicopter is described; the simulation was intended to investigate the validity of simulation for the representation of flight handling behaviour. Two areas were of concern: the representation of the Wessex within a limited computational capacity, and the suitable simulation of the flying environment so that handling characteristics were presented correctly to the pilots. By limiting the scope of the simulation to the normal flying regime of the helicopter, an adequate representation of the Wessex was possible. Presentation of handling behaviour was satisfactory in pitch and roll; some difficulties were experienced in the representation of yawing behaviour and of height control near the hover, and were attributed to inadequate motion capability of the simulator. The results of this simulation have been used to give confidence in the interpretation of future helicopter simulation. * Replaces RAE Technical Report 73096 - ARC 35005

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1299.pdf


    1285. Free-stream turbulence effects on the turbulent boundary layer

    R. L. Evans
    ARC/CP-1282
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1282.pdf


    1286. Gust loads on 707 and VC 10 aircraft

    I. W. Kaynes
    ARC/CP-1281
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1281.pdf


    1287. High subsonic flow past a steady two-dimensional aerofoil

    D. Nixon and G. J. Hancock
    ARC/CP-1280
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1280.pdf


    1288. Human engineering studies of high speed pedestrian conveyors

    A. C. Browning
    ARC/CP-1278
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1278.pdf


    1289. List of Current Papers Numbers 1251 - 1300


    ARC/CP-1300

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1300.pdf


    1290. Low-speed wind-tunnel tests on the lift-dependent drag of delta wings with conical camber

    D. L. I. Kirkpatrick, P. J. Butterworth
    ARC/CP-1293
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1293.pdf


    1291. Measurement of the internal performance of a rectangular air intake mounted on a fuselage at mach numbers from 1.6 to 2 part 4

    C. S. Brown, E. L. Goldsmith
    ARC/CP-1291
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1291.pdf


    1292. Non-linear stability theory of the flat plate boundary layer

    D. Corner, M. D. J. Barry and M. A. S. Ross
    ARC/CP-1296
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1296.pdf


    1293. Numerical studies on hypersonic delta wings with detached shock waves

    V. V. Shanbhag
    ARC/CP-1277
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1277.pdf


    1294. Results of a series of wind tunnel tests on the victor B.Mk.2 aircraft and a comparison with drag estimates and full scale flight data

    J. I. Simper
    ARC/CP-1283
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1283.pdf


    1295. SLR temperature measurements in the supersonic expansion of nitrogen in a shock-tunnel

    Michael J. Lewis and Leonard Bernstein
    ARC/CP-1294
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1294.pdf


    1296. Some predictions of crack propagation under combined cabin pressurisation and acoustic loadings

    W. T. Kirkby
    ARC/CP-1286
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1286.pdf


    1297. Some remarks on the induced velocity field of a lifting rotor and on Glauert's formula

    A. R. S. Bramwell
    ARC/CP-1301
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1301.pdf


    1298. Some results of wind-tunnel tests on an aerofoil section (NPL 9510) combining a 'peaky' upper surface-pressure distribution with rear loading

    D.J. Hall, V.G. Quincey and R.C. Lock
    ARC/CP-1292
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1292.pdf


    1299. Study of solid state remote control techniques as applied to the redesign of the electrical system in a large civil aircraft

    L. V. C. Jones
    ARC/CP-1289
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1289.pdf


    1300. The design of a series of warped slender wings for subsonic speeds

    Patricia J. Davies
    ARC/CP-1263
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1263.pdf


    1301. The development of rapid-testing techniques for flutter experiments

    K. W. Newman, C. W. Skingle and D. R. Gaukroger
    ARC/CP-1274
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1274.pdf


    1302. The external drag of fuselage side intakes rectangular intakes with compression surfaces vertical

    M. D. Dobson
    ARC/CP-1269
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1269.pdf


    1303. The influence of a single application of heat on fatigue crack propagation in DTD 5070A (RR58) aluminium alloy sheet

    F. E. Kiddle
    ARC/CP-1272
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1272.pdf


    1304. The nature, development and effect of the viscous flow around an aerofoil with high-lift devices

    D. N. Foster, P. R. Ashill, B. R. Williams
    ARC/CP-1258
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1258.pdf


    1305. The prediction of boundary-layer behaviour and profile drag for infinite yawed wings Part 1 a method of calculation

    B. G. J. Thompson, A. G. J. Macdonald
    ARC/CP-1307
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1307.pdf


    1306. The prediction of boundary-layer behaviour and profile drag for infinite yawed wings part 2 flow near a turbulent attachment line

    B. G. J. Thompson
    ARC/CP-1308
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1308.pdf


    1307. The prediction of boundary-layer behaviour and profile drag for infinite yawed wings part 3 calculations for a particular wing

    B. G. J. Thompson, G. A. Carr-Hill, M. Ralph
    ARC/CP-1309
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1309.pdf


    1308. The variability of fatigue damage from flight to flight

    N. I. Bullen
    ARC/CP-1297
    1974

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1297.pdf


    1309. A finite-difference scheme for computing supercritical flows in arbitrary coordinate systems

    C. M. Albone
    ARC/CP-1313
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1313.pdf


    1310. A non-axisymmetric end-wall boundary-layer theory for axial compressor rows

    J.W. Railly
    ARC/CP-1322
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1322.pdf


    1311. A short study of the effect of a penetrant oil on the fatigue life of a riveted joint

    P. H. O'Neill and R. J. Smith
    ARC/CP-1305
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1305.pdf


    1312. A theoretical and experimental investigation of the external-flow, jet-augmented flap

    P. R. Ashill
    ARC/CP-1319
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1319.pdf


    1313. An assessment of the accuracy of subsonic linearized theory for the design of warped slender wings

    Patricia J. Davies
    ARC/CP-1324
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1324.pdf


    1314. An investigation into the duty cycle of powered flying controls parts 1 and 2

    F. Holoubek
    ARC/CP-1312
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1312.pdf


    1315. Design and theoretical assessment of experimental glide path and flare systems for a BAC 1-11 aircraft (including direct lift control)

    F. R. Gill, M. J. Corbin
    ARC/CP-1337
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1337.pdf


    1316. Developments in the lifting surface theory treatment of symmetric planforms with a leading edge crank in subsonic flow

    B.L. Hewitt and W. Kellaway
    ARC/CP-1323
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1323.pdf


    1317. Fatigue crack propagation in thin sheets of L73 under constant strain amplitude

    P. H. O'Neill
    ARC/CP-1314
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1314.pdf


    1318. Free-flight model dynamic stability measurements on a 'not-so-slender' wing/fin combination at zero and small lift, M = 0.8 to 2.0

    G. H. Greenwood, Geraldine F. Edwards
    ARC/CP-1315
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1315.pdf


    1319. Interference problems on wing-fuselage combinations part 1 lifting unswept wing attached to a cylindrical fuselage at zero incidence in midwing position

    J. Weber
    ARC/CP-1331
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1331.pdf


    1320. Interference problems on wing-fuselage combinations part 2 symmetrical unswept wing at zero incidence attached to a cylindrical fuselage at zero incidence in midwing position

    J. Weber and M. G. Joyce
    ARC/CP-1332
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1332.pdf


    1321. Interference problems on wing-fuselage combinations part 3 symmetrical swept wing at zero incidence attached to a cylindrical fuselage

    J. Weber and M. G. Joyce
    ARC/CP-1333
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1333.pdf


    1322. Interference problems on wing-fuselage combinations part 4 the design problem for a lifting swept wing attached to a cylindrical fuselage

    J. Weber and M. G. Joyce
    ARC/CP-1334
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1334.pdf


    1323. Low-speed wind-tunnel tests of a two-dimensional wing fitted with two plain differentially-deflected trailing-edge flaps

    John Mckie
    ARC/CP-1326
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1326.pdf


    1324. Measurements of oscillatory aerodynamic hinge moments from the response of a wind tunnel model to turbulent flow

    G. B. Hutton, D. A. Drane, D. R. Gaukroger
    ARC/CP-1317
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1317.pdf


    1325. Measurements of pressure distribution on a half-model wing-body combination of 55 deg. sweep over a wide range of reynolds number

    K. G. Winter and J. B. Moss
    ARC/CP-1328
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1328.pdf


    1326. Measurements of secondary loss in a model turbine with variable inlet boundary layer

    J.D. Denton and C.G. Johnson
    ARC/CP-1335
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1335.pdf


    1327. Observations of the flow from a rectangular nozzle

    A. G. Kurn
    ARC/CP-1316
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1316.pdf


    1328. Systems of coordinates suitable for the numerical calculation of three-dimensional flow fields

    K. W. Mangler and J. C. Murray
    ARC/CP-1325
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1325.pdf


    1329. The characteristics of a family of rooftop aerofoils designed at their drag-rise condition in viscous, compressible flow part 1 design condition

    B. G. J. Thompson, S. W. Cosby
    ARC/CP-1320
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1320.pdf


    1330. The characteristics of a family of rooftop aerofoils designed at their drag-rise condition in viscous, compressible flow part 2 off design conditions

    B. G. J. Thompson, S. W. Cosby
    ARC/CP-1321
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1321.pdf


    1331. The development of portable coolers for the liquid conditioned suit

    G. F. Barlow
    ARC/CP-1330
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1330.pdf


    1332. The dynamic stability derivatives of a slender wing at zero and moderate lift a comparison of theory with free-flight model tests, M 0.8 to 2.0

    A. Jean Ross, Geraldine F. Edwards, A. P. Waterfall
    ARC/CP-1310
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1310.pdf


    1333. The effect of load dwells during fatigue crack propagation

    F. E. Kiddle
    ARC/CP-1318
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1318.pdf


    1334. The theory of partial retraction of imperfectly elastic ropes

    G.W.H. Stevens
    ARC/CP-1327
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1327.pdf


    1335. Thrust/drag analysis for a front fan nacelle having two separate co-axial exhaust streams

    P. G. Street
    ARC/CP-1311
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1311.pdf


    1336. Urea formaldehyde foamed plastic emergency arresters for civil aircraft

    G. M. Gwynne
    ARC/CP-1329
    1975

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1329.pdf


    1337. A control-surface oscillatory derivative rig for use with half-models in high-speed wind tunnels

    K. C. Wight and N. C. Lambourne
    ARC/CP-1353
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1353.pdf


    1338. A piloted flight simulation of the westland lynx

    T. Wilcock
    ARC/CP-1343
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1343.pdf


    1339. A practical approach to the prediction of oscillatory pressure distributions on wings in supercritical flow

    H. C. Garner
    ARC/CP-1358
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1358.pdf


    1340. A study of thermal fatigue acceleration in box beams under mechanical and thermal stress

    F. E. Kiddle, R. J. Kite and R. F. Mousley
    ARC/CP-1342
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1342.pdf


    1341. A theoretical investigation of high-speed axisymmetric turbulent mixing layers with large temperature differences

    P.W. Carpenter
    ARC/CP-1345
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1345.pdf


    1342. An application of fast frequency-sweep excitation to the measurement of sub-critical response of a low speed wind tunnel model

    C. W. Skingle and D. R. Gaukroger
    ARC/CP-1356
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1356.pdf


    1343. An assessment of the importance of the residual flexibility of neglected modes in the dynamical analysis of deformable aircraft

    A. S. Taylor and M. R. Collyer
    ARC/CP-1336
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1336.pdf


    1344. Evaluation of a loading form for the calculation of linearised theory pressure distributions in wings with control surfaces having swept hinge lines in steady subsonic flow

    T.G. Wigley
    ARC/CP-1340
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1340.pdf


    1345. Fortran programs for the determination of aerodynamic derivatives from transient longitudinal or lateral responses of aircraft

    A. Jean Ross, G. W. Foster
    ARC/CP-1344
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1344.pdf


    1346. Measurement of the internal performance of a rectangular air-intake at a mach number of 0.9

    C. S. Brown, E. L. Goldsmith
    ARC/CP-1346
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1346.pdf


    1347. Numerical methods for calculating unsteady flows in subsonic and supersonic turbomachinery cascades

    D.E. Hobson
    ARC/CP-1348
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1348.pdf


    1348. Planar incompressible flow over an aerofoil and its wake

    F. T. Smith
    ARC/CP-1352
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1352.pdf


    1349. Scatter in Fatigue:- Elements and Sections from Aircraft Structures

    A. M. Stagg
    ARC/CP-1357
    July 1969

    The fatigue test results, for elements and sections from the structures of aircraft, obtained by a number of experimenters are analysed in terms of the scatter present in the lives to fatigue failure. Data for structures made of any light alloy material and tested under any form of loading have been included in an attempt to increase the definition of any trends noted in the scatter, which was calculated using a log-normal distribution of fatigue lives as a basis. * Replaces RAE Technical Report 69155 - ARC 31639

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1357.pdf


    1350. Some results on the growth of instabilities in a shear layer

    Ann P. Dowling
    ARC/CP-1359
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1359.pdf


    1351. Stability theory of time-marching methods with extensions to the theory of ill-conditioning of steady-state methods

    S.M. Richardson
    ARC/CP-1383
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1383.pdf


    1352. The calculation, by a finite-difference method, of subcritical flow without circulation past a swept elliptic cylinder between walls

    G. J. Clapworthy
    ARC/CP-1393
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1393.pdf


    1353. The concept of load diffusion length in fibre reinforced composites

    E. H. Mansfield, Doreen R. Best
    ARC/CP-1338
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1338.pdf


    1354. The effect of geometry on the fatigue strength of aluminium alloy lugs / pcF. E. Kiddle


    ARC/CP-1349
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1349.pdf


    1355. The flutter of a two-dimensional wing with simple aerodynamics

    Ll. T. Niblett
    ARC/CP-1355
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1355.pdf


    1356. The influence of fibre distribution on the moduli of unidirectional fibre reinforced composites

    E. H. Mansfield
    ARC/CP-1347
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1347.pdf


    1357. The influence of fibre waviness on the moduli of unidirectional fibre reinforced composites

    E. H. Mansfield, D. Purslow
    ARC/CP-1339
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1339.pdf


    1358. The Prediction of Helicopter Rotor Hover Performance using a Prescribed Wake Analysis

    C. Young
    ARC/CP-1341
    June 1974

    A method of calculating the performance of a helicopter rotor in the hover is presented. The method combines the downwash velocity distribution induced by a contracting spiral vortex wake with strip element-momentum theory. The shape of the wake takes a prescribed geometry developed from an extensive series of model tests made in the USA. The predicted thrust and power is in good agreement with measurements made on model and full scale rotors provided that the aerofoil data is sufficiently well defined. The calculated load distribution along the blade is also compared with measurements made on Wessex helicopters. The load distribution is shown to be very sensitive to a light wind but theory compares well with experiment when this effect is eliminated. The hover performance predicted using only the wake induced velocity distribution is also discussed. The rotor performance is shown to be too sensitive to the geometry of the wake for the method to be used as a design tool with confidence, and the mathematical representation of the wake needs improving. * Replaces RAE Technical Report 74078 - ARC 35652.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1341.pdf


    1359. Wind tunnel flutter tests at subsonic speeds on a half-wing with a fan engine nacelle

    D. A. Drane and G. B. Hutton
    ARC/CP-1354
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1354.pdf


    1360. Wind-tunnel simulation of the effects of flight on radiated sound

    J. Jacques
    ARC/CP-1351
    1976

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1351.pdf


    1361. A comparative study of the fatigue performance of notched specimens of clad and unclad aluminium alloy, with and without a pre-stress

    P. R. Edwards and M. G. Earl
    ARC/CP-1361
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1361.pdf


    1362. A comparison of fatigue crack propagation rates in CM002 (Unclad RR58) aluminium alloy immersed in jet fuel and a fuel simulant

    F. E. Keates and R. F. Mousley
    ARC/CP-1365
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1365.pdf


    1363. A computer program for the interpolation and extrapolation of crack propagation data

    P. R. Edwards
    ARC/CP-1387
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1387.pdf


    1364. A strain modified 'steady-state' creep relationship for high strength aluminium alloy

    J. N. Webb
    ARC/CP-1367
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1367.pdf


    1365. A study of local stress histories in loaded and unloaded holes and their implications to fatigue life estimation

    J. E. Moon, B. H. E. Perrett, P. R. Edwards
    ARC/CP-1374
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1374.pdf


    1366. A system for the axial loading of creep specimens

    J. N. Webb
    ARC/CP-1364
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1364.pdf


    1367. A wind-tunnel investigation of the effects of flap span and deflection angle, wing planform and a body on the high-lift performance of a 28 degrees swept wing

    D. A. Lovell
    ARC/CP-1372
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1372.pdf


    1368. An influence-coefficient approach to static aeroelastic problems and a comparison with experiments on a flexible wind-tunnel model

    Dorothy M. Holford and A. S. Taylor
    ARC/CP-1379
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1379.pdf


    1369. Effect of interspersed periods of heating on fatigue crack initiation and propagation in CM001 (RR58) clad sheet

    F. E. Kiddle
    ARC/CP-1366
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1366.pdf


    1370. Effect of production modifications to rear of westland lynx rotor blade on sectional aerodynamic characteristics

    P. G. Wilby
    ARC/CP-1362
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1362.pdf


    1371. Experience of the Denton Blade-to-Blade Time Marching Computer Programs

    J.D. Bryce and M.R. Litchfield
    ARC/CP-1373
    September 1976

    computer programs have been used at NGTE to analyse the flow past transonic turbine blading. In this work experience has been gained in operating the programs and this paper describes the major findings in respect of how the programs have performed. Solutions for several blade sections, giving Mach number distribution, are included. *Replaces ARC 36909.

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1373.pdf


    1372. Fatigue behavior of bolted joints in RR58 aluminium alloy with and without interfay sealant

    F. E. Kiddle
    ARC/CP-1369
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1369.pdf


    1373. Fatigue testing with periodic heating - an investigation of some methods of acceleration

    A. K. Redfern, F. E. Kiddle
    ARC/CP-1368
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1368.pdf


    1374. Influence of prior heat and creep on fatigue in structural elements of DTD 5014 (RR58) aluminium alloy

    F. E. Kiddle
    ARC/CP-1375
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1375.pdf


    1375. Iterative calculation of flow past a thick cambered wing near the ground

    C. C. L. Sells
    ARC/CP-1370
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1370.pdf


    1376. Iterative design techniques for thick cambered wings in subcritical flow

    C. C. L. Sells
    ARC/CP-1371
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1371.pdf


    1377. List of Current Papers Numbers 1301 - 1350


    ARC/CP-1350

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1350.pdf


    1378. Numerical methods for two-dimensional and axisymmetric transonic flows

    M. J. Langley
    ARC/CP-1376
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1376.pdf


    1379. On three-dimensional flow in centrifugal impellers

    J. Moore, J.G. Moore and M.W. Johnson
    ARC/CP-1384
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1384.pdf


    1380. The application of the hilbert transform to system response analysis

    C. W. Skingle, K. H. Heron and D. R. Gaukroger
    ARC/CP-1378
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1378.pdf


    1381. The calibration of injector-powered engine simulators for use in pressurised wind tunnels

    A. Masson, D. N. Foster
    ARC/CP-1377
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1377.pdf


    1382. The current state of research and design in high pressure ratio centrifugal compressors

    P.M. Came
    ARC/CP-1363
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1363.pdf


    1383. The design and aerodynamic characteristics of the RAE 5215 aerofoil

    P. G. Wilby
    ARC/CP-1386
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1386.pdf


    1384. The effect of flight-by-flight load and temperature sequences on residual static strength of notched specimens in CM003 (RR58) aluminium alloy

    F. E. Kiddle
    ARC/CP-1360
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1360.pdf


    1385. The performance of a 6.5 pressure ratio centrifugal compressor having a radially-vaned impeller

    M.G. Jones
    ARC/CP-1385
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1385.pdf


    1386. The shear properties of unidirectional carbon fibre reinforced plastics and their experimental determination

    D. Purslow
    ARC/CP-1381
    1977

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1381.pdf


    1387. The Strength of Bolted Joints in Multi-Directional CFRP Laminates

    T. A. Collings
    ARC/CP-1380
    December 1975

    Tests have been carried out on simple bolted joints in multi-directional CFRP for a range of laminate configurations and hole sizes. For single-hole joints the various modes of failure have been isolated and the corresponding strengths measured; the effects of variables such as ply orientation, laminate thickness and bolt clamping pressure are discussed in the light of the results. Multi-hole joints have been designed using the single-hole data and test results show that for normal bolt spacings there is little interaction between holes. The results also show that the specific static strengths of these joints can be significantly better than those in conventional materials such as aluminium alloy and steel. * Replaces RAE Technical Report 75127 - ARC 36968

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1380.pdf


    1388. A mean camberline singularity method for two-dimensional steady and oscillatory aerofoils and control surfaces in inviscid incompressible flow

    B.C. Basu
    ARC/CP-1391
    1978

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1391.pdf


    1389. Impedance measurements on a spinning model helicopter rotor

    R. Cansdale, D. R. Gaukroger
    ARC/CP-1389
    1978

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1389.pdf


    1390. On the application of certain statistical methods to wind - tunnel testing

    J. McKie
    ARC/CP-1390
    1978

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1390.pdf


    1391. Through flow analysis of viscous and turbulent flows

    Apostolos Goulas and Roger C. Baker
    ARC/CP-1382
    1978

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1382.pdf


    1392. Two-dimensional aerofoils and control surfaces in simple harmonic motion in incompressible inviscid flow

    B.C. Basu and G.J. Hancock
    ARC/CP-1392
    1978

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1392.pdf


    1393. Wall boundary layers in cascades

    H. Marsh
    ARC/CP-1388
    1978

    Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1388.pdf


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