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AERADE Reports Archive ARC/CP listing 1.
CANCELLED AS CP 2.
PUBLICATION DISCONTINUED 3. 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 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 4. A comparison of three thick, symmetrical, multi-slot suction aerofoils N. Gregory and A. R. Curtis Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0020.pdf 5. A recording system for flight test data P. A. Hufton, F. G. R. Cook, and P. S. Saunders Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0044.pdf 6. Air bags as flexible supports in ground resonance testing of aircraft R.L. Moffat and d.R. Gaukroger Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0032.pdf 7. An approximate method for the estimation of the design point efficiency of axial flow turbines D.G. Ainley Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0030.pdf 8. An electronic analyser for linear differential equations J.J. Gait and D.W. Allen Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0023.pdf 9. Camber derivatives and two-dimensional tunnel interference at maximum lift R. C. Pankhurst and H. H. Pearcey Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0028.pdf 10. Determination of the static stability of seaplanes K.M. Tomaszewski Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0014.pdf 11. Full scale measurements of impact loads on a large flying boat part 1 description of apparatus and instrument installation J.W. McIver Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0182.pdf 12. Hydrodynamic design of seaplane floats K. M. Tomaszewski Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0015.pdf 13. Influence of variable specific heats on the high-speed flow of air J. Kestin Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0033.pdf 14. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0016.pdf 15. Maximum impact pressures on seaplane hull bottoms A. G. Smith, I. W. McCaig, W. M. Inverarity Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0004.pdf 16. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0009.pdf 17. Note on the interference on a part-wing mounted symmetrically on one wall of a wind-tunnel of octagonal section H. C. Garner Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0005.pdf 18. Preliminary measurements of the aerodynamic damping in pitch of a 12 ft diameter helicopter rotor C.M. Britland and R.A. Fail Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0022.pdf 19. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0007.pdf 20. Revised and extended performance characteristics of ram jets D.F. Collins and Frances M. Gordon Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0011.pdf 21. Some improvements in the design of thick suction aerofoils J. Williams Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0031.pdf 22. Some investigations into the design of wind tunnels with gas turbine jet engine drives H.J. Higgs 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 23. Some notes on the flapping motion of rotor blades J.B.B. Owen Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0001.pdf 24. Stability tests on a large scale model of the shetland hull bottom H. G. White, A. G. Smith Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0027.pdf 25. Tank tests on the effect of slipstream on the water performance of a large four engined flying boat (Shetland 1) S. Raymond Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0006.pdf 26. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0002.pdf 27. The annealing of formed perspex structures E.W. Russell Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0019.pdf 28. The application of jet propulsion to helicopters Wm. Stewart and M.F. Burle Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0008.pdf 29. The effect of propeller thrust on downwash and velocity at tailplane - a collection of data from low speed wind tunnel tests A. Spence Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0021.pdf 30. The effect of variation of air density and temperature on the airflow characteristics of porous fabrics J. Picken Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0025.pdf 31. The electronic simulator for the solution of flutter and vibration problems F. Smith Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0026.pdf 32. The heat treatment of flat perspex sheets E. W. Russell Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0018.pdf 33. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0010.pdf 34. The low speed performance of related aerofoils in cascade A. D. S. Carter 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0060.pdf 41. A three-channel piezo-electric pressure recorder P.J. Fletcher 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0047.pdf 47. Focussing Schlieren systems R.W. Fish and K. Parnham 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0062.pdf 57. Some effects of Reynolds number on a cambered wing at high subsonic Mach numbers H.E. Gamble 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 58. Swept-wing loading a critical comparison of four subsonic vortex sheet theories H. C. Garner, L. W. Bryant 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 59. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0040.pdf 60. Tests on the effect of incidence on some pressure heads at high subsonic speeds E. W. E. Rogers, and C. J. Berry Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0041.pdf 61. The air flow under the towing carriages in the R.A.E. seaplane tank K.M. Tomaszewski, S. Raymond, G.F. Chalmers Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0038.pdf 62. The design of Jettisonable cockpit hoods I. L. Keiller 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 63. The effect of induced velocity variation on helicopter rotor damping in pitch or roll G. J. Sissingh 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 64. The experimental approach to the problems of shaft whirling E. Downham Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0055.pdf 65. The incompressible potential flow past two-dimensional aerofoils with arbitrary surface suction W. T. Lord Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0056.pdf 66. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0059.pdf 67. The measurement of the derivative zw for an oscillating aerofoil A.L. Buchan, K.D. Harris, and P.M. Somervail Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0052.pdf 68. The supersonic pressure drag of a swept wing with a cranked maximum thickness line K. D. Thomson Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0061.pdf 69. The theoretical lift and pitching moment of a highly-swept delta wing on a body of elliptic cross-section T. Nonweiler Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0058.pdf 70. Torsional vibration investigations on the musketeer engine E. Downham, Winifred Davidson and M.O.W. Wolfe Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0034.pdf 71. Wind tunnel tests on a Griffith meteor model (without suction) D.A. Clarke Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0037.pdf 72. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0042.pdf 73. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0085.pdf 74. An assessment of the probable causes of variation of the speed correction coefficient of aircraft thermometers D. D. Clark Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0091.pdf 75. An experimental investigation of the performance of a pilot plant for drying air by solid granular adsorbents P.J. Bateman Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0079.pdf 76. Approximate two-dimensional aerofoil theory part 1 velocity distributions for symmetrical aerofoils S. Goldstein Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0068.pdf 77. Approximate two-dimensional aerofoil theory part 2 velocity distributions for cambered aerofoils S. Goldstein Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0069.pdf 78. Approximate two-dimensional aerofoil theory part 3 approximate designs of symmetrical aerofoils for specified pressure distributions S. Goldstein, and E. J. Richards Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0070.pdf 79. Approximate two-dimensional aerofoil theory part 4 the design of centre lines S. Goldstein Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0071.pdf 80. Approximate two-dimensional aerofoil theory part 5 the positions of maximum velocity and theoretical CL-ranges S. Goldstein Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0072.pdf 81. Approximate two-dimensional aerofoil theory part 6 aerofoils with hinged flaps S. Goldstein, and J. H. Preston Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0073.pdf 82. Calculated Pressure Distributions for the R.A.E. 100-104 Aerofoil Sections R. C. Pankhurst and H. B. Squire Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0080.pdf 83. Comparison of helicopter rotor model tests of aerodynamic damping with theoretical estimates G.J. Sissingh Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0098.pdf 84. Designing a slot for a given wall velocity A. Thom and Laura Klanfer Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0076.pdf 85. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0066.pdf 86. Digital recording and analysing of flight test data a proposed system E.J. Petherick Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0075.pdf 87. Draft corrections for water surface deflection under no.1 carriage of the R.A.E. seaplane tank T.B. Owen Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0067.pdf 88. Experiments on distributed suction through a rough porous surface Cambridge University Aeronautical Laboratory Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0084.pdf 89. Fatigue tests on typical two spar light alloy structures (meteor 4 tailplanes) under reversed loading K.D. Raithby Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0088.pdf 90. Flight tests on the Youngman-Baynes high-lift experimental aircraft D. Lean Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0065.pdf 91. Fluid dynamic notation in current use at N.G.T.E S. Gray Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0097.pdf 92. Graphical solution of multhopp's equations for the lift-distribution of wings F. Vandrey Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0096.pdf 93. Helicopter behaviour in the vortex ring conditions Wm. Stewart Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0099.pdf 94. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0078.pdf 95. Improper integrals in theoretical aerodynamics K.W. Mangler Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0094.pdf 96. List of current papers published for the Aeronautical Research Council (numbers 51-100) Aeronautical Research Council 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 97. N.P.L. Aerofoil catalogue and bibliography R. C. Pankhurst Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0081.pdf 98. Notes and graphs for boundary layer calculations in compressible flow W. F. Cope Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0089.pdf 99. Notes on the derivation of true air temperature from aircraft observations D. D. Clark Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0090.pdf 100. Power requirements for distributed suction for increasing maximum lift R. C. Pankhurst, and N. Gregory Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0082.pdf 101. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0086.pdf 102. Structural aspects of suction wings E.H. Mansfield Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0087.pdf 103. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0092.pdf 104. The diffusion of transverse loads in a reinforced circular cylinder with non-rigid frames S.R. Lewis Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0074.pdf 105. The Effect of Endplates on Swept Wings D. Kuchemann and D. J. Kettle Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0104.pdf 106. The effects of atmospheric humidity and temperature on the engine power and take-off performance of a hastings 1 G. Jackson Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0077.pdf 107. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0093.pdf 108. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0064.pdf 109. The natural frequencies of vibration of prismatic blades with particular reference to a 12 stage turbine R. Chaplin Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0095.pdf 110. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0083.pdf 111. A comparison of calculated and measured base pressures of cylindrically based projectiles W. F. Cope Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0118.pdf 112. A frost point hygrometer for supersonic wind tunnels D. Beastall and A. Winyard Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0106.pdf 113. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0114.pdf 114. A note on shock tubes D. W. Holder Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0110.pdf 115. A relaxation treatment of shock waves L. C. Woods Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0134.pdf 116. A review and assessment of various formulae for turbulent skin friction in compressible flow R. J. Monaghan Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0142.pdf 117. Air cooling methods for gas turbine combustion systems F. J. Bayley Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0133.pdf 118. An analysis of the air flow through the nozzle blades of a single stage turbine I.H. Johnston Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0131.pdf 119. An approximate method of deriving the transient response of a linear system from the frequency response C.A.A. Wass and E.G. Hayman Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0113.pdf 120. Asymmetric Tailplane Loads Due to Sideslip Winfried Braun Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0119.pdf 121. Charts of the wave drag of wings at zero lift T. Lawrence Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0116.pdf 122. Curves for estimating the wave drag of some bodies of revolution, based on exact and approximate theories L. E. Fraenkel Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0136.pdf 123. Design of a right-angled bend with constant velocities at the walls A. S. Thom Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0135.pdf 124. Effect of mean stress on the fatigue strength of D.T.D. 364 round bars with and without transverse holes G.M. Norris Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0120.pdf 125. Growth of the turbulent wake close behind an aerofoil at incidence D. A. Spence Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0125.pdf 126. Higher harmonics of flapping on the helicopter rotor W. Stewart Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0121.pdf 127. Low speed wind tunnel investigation of tab hinge moment characteristics W.J.G. Trebble and J.F. Holford Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0112.pdf 128. Measurement of lift, pitching moment and hinge moment on a two-dimensional RAE 102 aerofoil A. S. Batson Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0191.pdf 129. Method for the determination of the pressure distribution over a finite thin wing at a steady low speed G. J. Hancock Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0128.pdf 130. Note on the lift slope, and some other properties, of delta and swept-back wings E. F. Relf Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0127.pdf 131. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0137.pdf 132. Pressure error measurement using the formation method K.C. Levon Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0126.pdf 133. Some curves for use in calculations of the performance of conical centrebody intakes at supersonic speeds and at full mass flow L.E. Fraenkel Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0108.pdf 134. Surface slopes and curvatures of the RAE 100-104 and other rooftop-type aerofoil sections J. Williams and Edna M. Love Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0129.pdf 135. Tail plane loads and normal accelerations after an automatic control failure J.L. Reddaway Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0111.pdf 136. Tests on an axial compressor with various stator blade staggers R.A. Jeffs, E.L. Hartley and P. Rooker Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0132.pdf 137. The application of the polygon method to the calculation of the compressible subsonic flow round two-dimensional profiles L. C. Woods Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0115.pdf 138. The definitions of the angles of incidence and of sideslip C.H.E. Warren Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0124.pdf 139. The estimation of skin temperatures attained in high speed flight F.V. Davies and R.J. Monaghan Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0123.pdf 140. The low speed performance of a helicopter A. L. Oliver Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0122.pdf 141. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0139.pdf 142. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0140.pdf 143. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0130.pdf 144. The pressures on the surface of a flat elliptic cone set symmetrically in a supersonic stream D. G. Hurley Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0109.pdf 145. The theory of aerofoils with hinged flaps in two-dimensional compressible flow L. C. Woods Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0138.pdf 146. The vibrations of a swept wing N.S. Heaps 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0165.pdf 153. A variable inductance acceleration transducer H.K.P. Neubert 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 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 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 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 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 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 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 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 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 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 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 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
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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0171.pdf 173. The effect of compressibility on elevator flutter D. E. Williams 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0154.pdf 183. The technique of flutter calculations H. Templeton 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0147.pdf 187. Unsteady cavitating flow past curved obstacles L. C. Woods Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0149.pdf 188. Vibration and flutter of aircraft aerials W. H. Johnson 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0187.pdf 199. Correlated fatigue data for aircraft structural joints R.B. Heywood 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0206.pdf 201. Flutter calculations on a resonance model delta wing H. Hall Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0260.pdf 202. Further experiments with a slotted-wall test section F. Vandrey 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0212.pdf 214. Models for aero-elastic investigations H. Templeton 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0193.pdf 235. Theory of the broad-bladed propeller G. I. Ginzel 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0286.pdf 240. A corrected speed tachoscope R. Staniforth 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0301.pdf 258. Flow direction measurements in supersonic wind tunnels D. J. Raney 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0305.pdf 272. On the stability of a laminar wake C. H. McKoen Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0303.pdf 273. Optimum designs for reinforced circular holes E. H. Mansfield 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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. 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0299.pdf 304. Turbulence encountered by comet 1 aircraft J.R. Heath-Smith Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0248.pdf 305. Turbulent diffuser flow B. S. Stratford 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0241.pdf 308. Vibration and flutter flight testing M. O. W. Wolfe 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0320.pdf 314. A note on some integrals in aerodynamics D.E. Williams 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0374.pdf 320. An experimental introduction to the jet flap N. A. Dimmock 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0362.pdf 323. Atmospheric turbulence encountered by Hermes aircraft J.R. Heath-Smith 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0363.pdf 332. Flutter calculations on a supersonic aircraft wing Ll. T. Niblett Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0328.pdf 333. Flutter prediction in practice E. G. Broadbent 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 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 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 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 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 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 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 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 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 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 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
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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0326.pdf 348. Notation for rotorcraft work A. Armitage 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0319.pdf 355. Some further jet flap experiments N. A. Dimmock 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0317.pdf 358. Supports for vibration isolation W. G. Molyneux 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0394.pdf 384. Automatic data reduction equipment for wind tunnels G. C. Rowley 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0385.pdf 387. Complex variable applications to certain coupled systems D. P. Jenkins 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0421.pdf 428. A survey of buffeting loads Diana M. Seal 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0438.pdf 446. On boundary-layer transition wires J. C. Gibbings 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0485.pdf 522. The aerodynamic drag of near earth satellites G. E. Cook 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0533.pdf 551. Automatic control of laboratory representation of kinetic heating J. Taylor Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0532.pdf 552. Beating the heat barrier J. Taylor 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0602.pdf 579. Scale models for thermo-aeroelastic research W. G. Molyneux 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0539.pdf 585. The analysis of complex vibrations with spada S. L. Entres 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0616.pdf 610. Diffraction of oblique shock wave R. S. Srivastava 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0597.pdf 612. Gusts at low altitude in North Africa N. I. Bullen Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0581.pdf 613. Inflatable servo actuators A.R. Mettam 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0658.pdf 625. Slender not-so-thin wing theory J. C. Cooke Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0659.pdf 626. Some three-dimensional effects of rotating stall S. L. Dixon 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0636.pdf 648. Boundary layer characteristics of caret wings D. Catherall 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0614.pdf 650. Diffraction of a plane straight shock wave R. S. Srivastava 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0680.pdf 660. On theoretical plasticity and crack propagation E. H. Mansfield 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0637.pdf 681. Three-dimensional turbulent boundary layers J. C. Cooke 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0744.pdf 695. Aeroelastic problems of high speed aircraft D. Moxon 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0678.pdf 710. Limit analysis of circular frames E. O. Imegwu Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0705.pdf 711. List of current papers (numbers 601-650) Aeronautical Research Council 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0741.pdf 721. Notes on Ducted Fan Design R. C. Turner 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0752.pdf 723. On the numerical calculation of theodorsen's transformation B. Thwaites Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0691.pdf 724. On the theory of vibrational relaxation in gases E. Wild 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0733.pdf 727. Prandtl-Meyer flow in a relaxing gas P. A. Blythe 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0715.pdf 756. A digital recording system for structural research D. Purslow 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0823.pdf 760. A problem of wing-body interference D. G. Randall 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0795.pdf 766. Alleviation of thermal stresses in aircraft structures E. C. Capey 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0812.pdf 788. List of current papers (numbers 651-700) Aeronautical Research Council Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0700.pdf 789. List of current papers (numbers 701-750) Aeronautical Research Council Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0750.pdf 790. List of current papers (numbers 751-800) Aeronautical Research Council 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0703.pdf 815. The chance of a rough flight N. I. Bullen 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0833.pdf 844. A survey of unsteady hypersonic flow problems B. M. Wood 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0723.pdf 881. Supersonic laminar boundary layers on cones J. C. Cooke 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0839.pdf 888. The lateral oscillation of slender aircraft A. J. Ross 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 time response stagnation temperature probe R. A. East and J. H. Perry Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0909.pdf 918. A simple flexible supersonic wind tunnel nozzle for the rapid and accurate variation of flow mach number D. Pierce Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0865.pdf 919. A study on the running times in reflected shock tunnels J. A. D. Ackroyd Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0883.pdf 920. A survey of the mechanics of uniaxial creep deformation of metals J.W.L. Warren Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0919.pdf 921. A theoretical investigation of the effect of aspect ratio on axial flow compressor performance J. H. Horlock and G. J. Fahmi Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0943.pdf 922. A turbulent skin-friction law for use at subsonic and transonic speeds J. F. Nash and A. G. J. Macdonald Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0948.pdf 923. A use of arbitrary modes in control-surface flutter investigations T. Niblett Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0928.pdf 924. Aircraft loading actions problems - proceedings of a symposium held at Farnborough on 28 October 1966 A. S. Taylor and D.J. Eckford 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 925. An analogue computer for on-line correction of wind tunnel force and moment data B. E. Pecover Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0946.pdf 926. An analysis of some major factors involved in normal take-off performance D. H. Perry 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 927. An EMA program for the analysis of plane stress problems Jane Buller-Sinfield 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 928. An experiment in turbine blade profile design I. H. Johnston and Diane Smart Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0941.pdf 929. An experimental investigation of the two-dimensional wall jet James H. Whitelaw Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0942.pdf 930. An investigation into a technique for measuring jet interference effects using free-flight models G. H. Greenwood Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0969.pdf 931. An investigation of stress redistribution caused by creep in a thick-walled circular cylinder subjected to axial and thermal loading J. M. Clarke 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 932. Approximate solutions of the three-dimensional laminar boundary layer momentum integral equations P.D. Smith and A.D. Young 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 933. Atmospheric turbulence and aircraft height-keeping accuracy B. A. M. Piggott 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 934. Balance measurements (excluding drag) on a delta wing aircraft at transonic speeds M. M. Shaw Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0904.pdf 935. Calculation of compressible turbulent boundary layer on a flat plate S. V. Patankar 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 936. Camber effects on the non-linear lift of slender wings with sharp leading edges L. C. Squire Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0924.pdf 937. Characteristics of high-speed wind tunnels in the United Kingdom relevant to aeroelastic-model tests C. A. K. Irwin Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0876.pdf 938. Civil aircraft airworthiness data recording programme study of severe turbulence encountered by civil aircraft G. E. King Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0974.pdf 939. Computer programmes to calculate the response of flexible aircraft to gusts and control movements C. G. B. Mitchell Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0957.pdf 940. Crack propagation in fatigue. Some experiments with DTD 5070A aluminium alloy sheet D. P. Rooke et al Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0896.pdf 941. Crack propagation tests on 2024-T3 unstiffened aluminium alloy panels of various length-width ratios T. J. Carter Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0952.pdf 942. Determination of stagnation temperatures in the R.A.R.D.E. hypersonic gun tunnel from streak camera measurements of flow velocity J. E. Bowman Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0929.pdf 943. Estimation of surface pressures from observed shock-wave envelopes surrounding conical bodies at M = 4.0 M. J. Larcombe 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 944. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0925.pdf 945. 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 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 946. Forces on cone cylinders at M = 3.98 K.C. Moore 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 947. Free-flight measurements of the incremental drag due to engine nacelles on a transonic swept-wing aircraft G. K. Hunt Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0960.pdf 948. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0934.pdf 949. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0965.pdf 950. Investigation of the normal force characteristics of slender delta wings with various rhombic cross-sections in subsonic conical flow D. L. I. Kirkpatrick Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0922.pdf 951. List of current papers (numbers 801-850) Aeronautical Research Council Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0850.pdf 952. List of current papers (numbers 851-900) Aeronautical Research Council Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0900.pdf 953. List of current papers (numbers 901-950) Aeronautical Research Council Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0950.pdf 954. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0916.pdf 955. Low-speed measurements of skin friction on a large half-model slender wing L. A. Wyatt, L. F. East 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 956. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0869.pdf 957. Measurement of the internal drag of air breathing installations on slender wing-body combinations at supersonic speeds J. W. Britton Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0914.pdf 958. Measurement of the moments of inertia of the handley page HP115 aircraft L. J. Fennell Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0907.pdf 959. Measurements of buffeting on slender wing models D. G. Mabey Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0917.pdf 960. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0958.pdf 961. Measurements of pressure distribution and shock-wave shape on power-law bodies at a mach number of 6.85 D.H. Peckham Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0871.pdf 962. Measurements of wing buffeting on a scimitar model D. G. Mabey Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0954.pdf 963. More tests with a variable ramp intake having a design mach number of 2.2 M. C. Neale and P. S. Lamb Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0938.pdf 964. Nitrogen condensation in the R.A.R.D.E. hypersonic gun tunnel J. E. Bowman Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0956.pdf 965. On the breakdown of near-equilibrium quasi-one-dimensional flow P. A. Blythe Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0923.pdf 966. On the flexure of a conical frustum shell E. H. Mansfield 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 967. Potential flow theory for tandem cascade by Howell's method Y. M. Yip and J. W. Railly Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0971.pdf 968. Project topcat power spectral measurements of clear air turbulence associated with jet streams Anne Burns, C. K. Rider Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0940.pdf 969. Random and systematic factors in the scatter of creep data K. F. A. Walles Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0935.pdf 970. Short-cowl front-fan turbojets friction drag and wall-jet effects on cylindrical afterbodies J. E. Green 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 971. Some comments on the conditions in a local supersonic flow region T. H. Moulden 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 972. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0889.pdf 973. Some further notes on the laminar boundary layer development and running time in a shock tube J. A. D. Ackroyd Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0966.pdf 974. Some notes on fuel boiling losses and fuel-tank pressurisation in a long-range supersonic aircraft W. G. S. Lester 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 975. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0936.pdf 976. Some theoretical studies concerning oleo damping characteristics H. Hall Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0951.pdf 977. Stability and control flight testing - some of the test instrumentation requirements R. Rose 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 978. Stiffness, damping and creep properties of a polyurethane foam including the effects of temperature and humidity D. B. Payen Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0905.pdf 979. Studies of flow fields created by vertical and inclined jets when stationary or moving over a horizontal surface W. A. Abbott Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0911.pdf 980. Studies of the flow fields created by single vertical jets directed downwards upon a horizontal surface M. Cox and W. A. Abbott Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0912.pdf 981. Supersonic flutter derivatives for a series of swept and cropped delta wings G.Z. Harris Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0920.pdf 982. Symposium on the use of the digital computer in aircraft structural design and analysis G. G. Pope Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0926.pdf 983. Techniques for tests on structures subject to kinetic heating P. Talbot Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0970.pdf 984. Tests at M = 1.82 on an engine installation with boundary-layer diverter for a slender gothic wing R. T. Griffiths, E. L. Goldsmith 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 985. Tests on an engine installation for a slender gothic wing at M = 1.82 R. T. Griffiths Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0866.pdf 986. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0937.pdf 987. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0939.pdf 988. The accuracy of pressure transducers when used in short-duration wind tunnel facilities L. Pennelegion, K. Wilson and B. Redston Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0949.pdf 989. The application of non-dimensional methods to the planning of helicopter performance flight trials and the analysis of results P. A. Knowles Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0927.pdf 990. The breakdown of certain types of vortex N. C. Lambourne Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0915.pdf 991. The calculation of momentum thickness in a turbulent boundary layer at mach numbers up to unity J. F. Nash and A. G. J. Macdonald Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0963.pdf 992. The calculation of the pressure distribution on a thick cambered aerofoil at subsonic speeds including the effects of the boundary layer B. J. Powell 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 993. The derivation of power spectra of density variations in hypersonic wakes from schlieren photographs J. P. Thompson 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 994. The development at Cranfield of a free piston compression shock tube M.J. Pratt 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 995. The distribution of a wall pressure rise in a turbulent boundary layer R.J. Herd Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0967.pdf 996. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0968.pdf 997. The effect of base bleed on the base pressure of several shrouded and unshrouded propelling nozzles at M∞ = 1.96 M.M. Shaw Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0962.pdf 998. The effects of extended practice on performance in a tracking task R.C. Hornby and R. Wilson 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 999. The influence of density gradients on the effectiveness of film cooling B. R. Pai and J. H. Whitelaw 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 1000. The influence of gas streams and magnetic fields on electric discharges part 3 arcs in transverse magnetic fields at atmospheric pressure V. W. Adams Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0959.pdf 1001. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0881.pdf 1002. The Longitudinal Characteristics of Three Slender "Mild Ogee" Wings at Mach Numbers from 0.4 to 2.0 D.G. Mabey, G.P. Ilott 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 1003. The performance of an aerofoil in stationary and rotating cascades E. C. Deverson, H. Marsh and J. T. B. Oxford 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 1004. The pressure drag of an aerofoil with six different round leading edges, at transonic and low supersonic speeds P. G. Wilby Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0921.pdf 1005. The Range Performance of Hypersonic Aircraft D. H. Peckham and L. F. Crabtree 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 1006. The spectral energy balance in a turbulent mixing layer P. Bradshaw and D. H. Ferriss Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0899.pdf 1007. The thermal assessment of personal conditioning garments D. R. Burton Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0953.pdf 1008. The velocity field near non-lifting delta wings according to supersonic linearized theory R. S. Bartlett Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0961.pdf 1009. Thermal conductance tests on cabin wall insulation assemblies for a supersonic transport aircraft Ian I. McNaughtan and P. A. Keene Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0910.pdf 1010. Viscosity effects on the two-dimensional flow in cascades J. P. Gostelow, A. K. Lewkowicz and M. R. A. Shaalan Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0872.pdf 1011. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0903.pdf 1012. Wind tunnel tests on a rectangular, twin duct, variable geometry air intake at supersonic speeds M. D. Dobson Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0944.pdf 1013. Wind tunnel tests on six wing-body models at M = 4 J. Pike 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 1014. A control and measurement system for aeroelastic model tests W. D. T. Hicks 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 1015. A critical examination of the use of a two-dimensional turbulent profile family to represent three-dimensional boundary layers N.A. Cumpsty 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 1016. A marching procedure for the determination of inviscid two-dimensional sonic flow past a blunt symmetrical body D. G. Randall Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0992.pdf 1017. A method for the prediction of the probabilities of aircraft fatigue failures within a fleet of known size A. M. Stagg 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 1018. A Note on some Static Tests of Flexible Skirts for Hovercraft W. G. S. Lester ond F. T. Kiernan 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 1019. A piloted flight simulator study of speed instability during the landing approach D.H. Perry Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0980.pdf 1020. A survey of fluid flow and heat transfer in rotating ducts Henry Barrow 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 1021. A survey of the infrared radiation properties of carbon dioxide J. P. Hodgson Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0981.pdf 1022. A survey of the thermal conductance of metallic contacts H. Y. Wong Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0973.pdf 1023. A theoretical investigation for delta wings with leading-edge separation at low speeds R. K. Nangia and G. J. Hancock 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 1024. An experimental investigation of laminar heat transfer in a uniformly heated tube rotating about a parallel axis W. D. Morris 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 1025. An investigation of the rolling moments due to sideslip on high tailplanes at subsonic, transonic and supersonic speeds D. G. Mabey Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0999.pdf 1026. Cabin conditioning tests on a simulated M 2.2 transport aircraft cabin T. L. Hughes, E. A. Timby Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0976.pdf 1027. Calculation of the response of a transport aircraft to continuous turbulence and discrete gusts and a comparison with flight measurements C. G. B. Mitchell 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 1028. 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 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 1029. Comparison of different methods of assessing the free oscillatory characteristics of aeroelastic systems A. Jocelyn Lawrence, P. Jackson 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 1030. Correlation of voltage-current characteristics of wall-stabilised, free-burning and cross-flow arcs W. T. Lord Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0996.pdf 1031. Crossflow in turbulent boundary layers N. A. Cumpsty 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 1032. Design of a symmetrical section with specified pressure distribution C. C. L. Sells 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 1033. Discrete element analysis of the lateral vibration of rectangular plates in the presence of membrane stresses D. J. Dawe 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 1034. Drag measurements on a series of afterbodies at transonic speeds showing the effect of sting interference A. G. Kurn Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0984.pdf 1035. Experiments on methods for the numerical solution of a certain non-linear biharmonic equation M. R. Abbott Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0979.pdf 1036. Finite difference solutions for an unsteady interference parameter in slotted wind tunnels K.R. Rushton and Lucy M. Laing 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 1037. Flight measurements of wing-tip vortex motion near the ground F.W. Dee, O.P. Nicholas 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 1038. Free flight measurements of the longitudinal stability of a transonic swept-winged aircraft G. K. Hunt 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 1039. Further analysis of TSR 2 flights through turbulence T.B. Saunders Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0997.pdf 1040. Gradient properties of a model of stationary random turbulence J. G. Jones Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0998.pdf 1041. Guided weapons aerodynamic study force and moment measurements on some monoplane and cruciform slender wing-body combinations at M 4. 0 P. L. Roe Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0972.pdf 1042. Heat transfer in a tube revolving about a displaced axis J.F. Humphreys 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 1043. Inflated mobile lifting structures practical design and trials of a circular planform model using membrane construction A. Y. Simpson 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 1044. Leading edge effects on caret wings J. C. Cooke Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0978.pdf 1045. List of current papers (numbers 1051-1100) Aeronautical Research Council Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1100.pdf 1046. Loads experienced in turbulence by a central African airways viscount without and with cloud warning radar N.I. Bullen, Judy E. Aplin 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 1047. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0994.pdf 1048. Low-speed wind-tunnel tests of a number of fin configurations on a flat-plate gothic wing of unit aspect ratio D. H. Peckham 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 1049. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0983.pdf 1050. Measurements of fluctuating pressures in and behind the bomb bay of a Canberra Aircraft C. W. Skingle, N. M. Willcox, D. R. Gaukroger 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 1051. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0985.pdf 1052. Measurements of secondary flow in the boundary layers of a 180 degree channel V.C. Patel 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 1053. Measurements of the effects of thickness on vortex breakdown position on a series of sharp-edged delta wings P. B. Earnshaw 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 1054. Methods of solving the flutter equations in use at R.A.E T. Niblett 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 1055. Numerical solutions of hypersonic near-wake flow by the particle-in cell method R. I. Crane 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 1056. 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 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 1057. On the equilibrium piston technique in gun tunnels L. Davies, J.D. Regan and K.A. Dolman Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0982.pdf 1058. On the prediction of laminarisation B. E. Launder and W. P. Jones 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 1059. Optimum fibre arrangements for reinforced sheets under combined loading G. Z. Harris Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0975.pdf 1060. Performance estimates for a reflected-shock tunnel with a modified driver to produce high test-section Reynolds numbers J. G. Woodley 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 1061. Solution of the catapult take-off performance equations by an analogue method E. W. Addicott, R. W. Jones Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0977.pdf 1062. The calculation of sub-critical pressure distributions on symmetric aerofoils at zero incidence P. G. Wilby Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0993.pdf 1063. The correlation and prediction of pressure distributions on compression surfaces of sharp-edged conical bodies at high supersonic speeds M. J. Larcombe 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 1064. The development of a dummy bird for use in bird strike research A. W. R. Allcock and D. M. Collin 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 1065. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0995.pdf 1066. The effect at M = 1.7 of removing swept endwalls from a wedge compression intake M. M. Shaw 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 1067. The effect of initial conditions on the development of turbulent boundary layers P. Bradshaw and D. H. Ferriss Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0986.pdf 1068. The influence of gas streams and magnetic fields on electric discharges part 4 arcs moving along straight parallel electrodes V. W. Adams Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0987.pdf 1069. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0988.pdf 1070. The local pressure field of turbulent jets P. O. A. L. Davies, N. W. M. Ko and B. Bose Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0989.pdf 1071. 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 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 1072. The pressure distribution at zero-lift on a slender delta wing at transonic speeds M. C. P. Firmin Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/0991.pdf 1073. The stability of boundary conditions in the numerical solution of the time-dependent Navier-Stokes equations P. J. Taylor 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 1074. The use of calibrated strain gauges for flight load determination P. B. Hovell, D. A. Webber, T. A. Roberts 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 1075. Wall corrections to longitudinal components measured on wind-tunnel models with tails D. A. Lovell 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 1076. Wind tunnel investigation of jet interference for underwing installation of high bypass ratioengines D. J. Raney, A. G. Kurn, J. A. Bagley 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 1077. A preliminary experiment in resonance testing a rotating blade C. W. Skingle, D. R. Gaukroger, G. A. Taylor 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 1078. Civil aircraft airworthiness data recording programme special events related to airspeed control practices (February 1963 to February 1966) CAADRP special events working party 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 1079. Civil aircraft airworthiness data-recording programme. Special events relating to handling and control (January 1963 to February 1966) CAADRP special events working party 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 1080. Cumulative fatigue damage studies of pinned-lug and clamped-lug structural elements in aluminium alloy W. T. Kirkby and P. R. Edwards 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 1081. Gusts, discrete and indiscrete N. I. Bullen 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 1082. List of current papers published for the aeronautical research council (numbers 1001-1050) Aeronautical Research Council 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 1083. List of current papers published for the Aeronautical Research Council (numbers 951 - 1000) Aeronautical Research Council 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 1084. Low altitude turbulence measurements over land and sea during flights in a Canberra aircraft E. W. Wells 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 1085. Modification of a normal shock by electrostatic forces G. F. Butler 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 1086. Nonlinear structural dynamics problems in aeronautics A. Simpson 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 1087. The airborne path during take-off for constant rate-of-pitch manoeuvres D. H. Perry 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 1088. 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 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 1089. The influence of elevator movement on the normal accelerations experienced by a transport aircraft in moderate turbulence D. J. Eckford 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 1090. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1090.pdf 1091. A compressive test specimen for unidirectional carbon fibre reinforced plastics P. D. Ewins Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1132.pdf 1092. A Discussion of some Jet - Lift V/STOL Aircraft Characteristics and their likely Effect on Operational Applications D. Lean 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 1093. A method of correlating the ground effects on the longitudinal characteristics of slender wings D. L. I. Kirkpatrick Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1095.pdf 1094. A short static probe with good incidence characteristics at supersonic speed I. S. Donaldson and D. J. Richardson Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1099.pdf 1095. A wind-tunnel investigation of the stalling performance of two compressor cascades of different aspect ratios at low speed M. R. A. Shaalan Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1103.pdf 1096. Airflow rate requirements in passenger aircraft E. A. Timby Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1136.pdf 1097. Algol programmes for the response analysis of linear systems with deterministic or random inputs L. J. Hazlewood, E. Huntley Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1124.pdf 1098. An inflated mobile lifting system for an 8 ton load I. S. H. Brown, F. T. Kiernan Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1092.pdf 1099. An investigation of the scatter in constant amplitude fatigue test results of aluminium alloys 2024 and 7075 A. M. Stagg Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1093.pdf 1100. An investigation of the scatter in variable-amplitude fatigue-test results of 2024 and 7075 materials A. M. Stagg Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1123.pdf 1101. An investigation of the stresses in a wind tunnel corner section D. E. W. Stone, P. S. A. Baxter Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1117.pdf 1102. An outline guide to criteria for the limitation of urban noise D. W. Robinson Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1112.pdf 1103. Atmospheric gusts a review of the results of some recent R.A.E. research J. Burnham Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1091.pdf 1104. Cabin air requirements for crew comfort in military aircraft T. L. Hughes Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1094.pdf 1105. Civil aircraft airworthiness data recording programme some characteristics of severe turbulence G. E. King Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1098.pdf 1106. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1135.pdf 1107. Delta wings with longitudinal camber at low speed R. K. Nangia and G. J. Hancock Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1129.pdf 1108. Effects of suction on the interaction between shock wave and boundary layer at a compression corner L. H. Tanner and S. L. Gai 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 1109. Experimental investigation of the effect of trailing-edge sweepback on the subsonic longitudinal characteristics of slender wings D. L. I. Kirkpatrick, A. G. Hepworth Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1130.pdf 1110. Flight tests to investigate the problems of steep approaches by stol aircraft C. O. O'Leary, N. V. Slatter Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1138.pdf 1111. Gust response measurements on a model aircraft R. Cansdale, H. Hall Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1113.pdf 1112. Influence of wing root shaping on the pressure distribution of swept-wing body configurations J. Bridgewater and K. H. Wilson Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1109.pdf 1113. Ingestion of Debris into Intakes by Vortex Action D. E. Glenny and N. G. T. E. Pyestock 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 1114. Interference effects at M = 8.5 of wires and probes on the wake of a magnetically suspended rounded base cone J. F. W. Crane Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1133.pdf 1115. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1111.pdf 1116. Laminar boundary layer calculations compared with measurements by hummel J.C. Cooke Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1096.pdf 1117. Liquid and vapour cooling systems for gas turbines J P Edwards Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1127.pdf 1118. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1105.pdf 1119. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1106.pdf 1120. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1107.pdf 1121. Low-speed characteristics of waverider wings R. F. A. Keating, B. L. Mayne Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1118.pdf 1122. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1097.pdf 1123. 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1108.pdf 1124. Non-equilibrium emissivity of carbon dioxide near 4.3 mu J.P. Hodgson Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1116.pdf 1125. Normal shock-wave tables for air, argon, carbon dioxide, carbon monoxide, hydrogen, nitrogen, nitrous oxide, and oxygen K. C. Lapworth Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1101.pdf 1126. Operational and theoretical studies on the effect of pilot action on heavy landings H. Hall, G. B. Hutton Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1119.pdf 1127. Preliminary flight assessment of the low-speed handling of the BAC 221 ogee-wing research aircraft C. S. Barnes, O. P. Nicholas Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1102.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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1143.pdf 1142. A parallel motion creep extensometer J. N. Webb 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 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 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 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 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 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 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, 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. 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1163.pdf 1166. Notes on the diffraction of sound J. C. Cooke 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1170.pdf 1176. Scale effects on oscillatory control-surface derivatives A. W. Moore 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1160.pdf 1179. Some observations on vortex shedding and acoustic resonances M. Gaster 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1215.pdf 1206. Andover C. Mk. 1 airfield criteria trials J. Howell 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1229.pdf 1210. Dynamic calibration of gas flowmeters K. R. Maslen 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 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 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 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. Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1216.pdf 1214. Fortran subroutines for finite element analysis B. C. Merrifield 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1212.pdf 1216. List of Current Papers Numbers 1151-1200
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
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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1219.pdf 1229. The dynamic behaviour of crash helmets J.M. Rayne 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1203.pdf 1236. Transonic fan noise D. Hawkings 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1244.pdf 1246. Decay of trailing vortices E. H. Oon Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1238.pdf 1247. Gust loads on comet aircraft I. W. Kaynes Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1247.pdf 1248. List of current papers (numbers 1201-1250) Aeronautical Research Council 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 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. 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 Available from: http://naca.central.cranfield.ac.uk/reports/arc/cp/1285.pdf 1271. An aeroelastic model helicopter rotor R. Cansdale 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 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 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 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 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 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 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 A survey has been made of techniques for producing multiaxial stressconditions 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. 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 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 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 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 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 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 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 conce |