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Now showing items 1115-1134 of 1313

Tables of multhopp and other functions for use in lifting-line and lifting-plane theory

V. M. Falkner; E. J. Watson (1948)

The report gives the derivation and computed tables of two classes of functions suitable for the solution of problems of spanwise aerodynamic loading of wings either by lifting-line or lifting-plane theory. The functions ...
Tables of supersonic symmetrical flow around right circular cones, with and without the addition of heat at the wave

R. S. Bartlett (1966)

The generalised relations for shock, strong detonation and Chapman-Jouguet detonation waves are used to determine the flow variables behind an attached conical shock wave. The non-linear ordinary differential equations of ...
Take-off tests on a transport aircraft including the use of a 'SCAT' take-off director

C. O. O'Leary; J. N. Cannell; R. L. Maltby (1966)

A large number of take-off tests have been made on a Comet aircraft with the object of (a) acquiring comprehensive data on undirected take-offs; (b) testing a SCAT take-off director. SCAT is explained in detail and the ...
Tank Tests on a Hull with the Main Step Faired in Planform and Elevation

D. I. T. P. Llewelyn-Davies (1945)

Tank tests were required to find out whether the water characteristics of a hull with a main step, faired in both planform and elevation, were comparable with those of a hull with a conventional Vee or transverse step. ...
Tank tests on a jet-propelled boat-seaplane fighter (saunders-roe E6/44)

G. L. Fletcher (1946)

Investigations into porpoising stability, water resistance, and seaworthiness have been made on the hull design of the E6/44. The original lines were unsatisfactory for seaworthiness and porpoising stability at overload ...
A technique for analysing the results of a flutter calculation

J. C. A. Baldock (1973)

A technique is presented for condensing a multi-degree-of-freedom flutter calculation so that similar flutter conditions are achieved with two degrees-of-freedom. Use is made of digital computer programmes, and the process ...
Technique for flutter tests using ground-launched rockets, with results for unswept wings

W. G. Molyneux; F. Ruddlesden; P. J. Cutt (1951)

A technique for the investigation of wing flutter by means of ground-launched rockets is described. An important feature of the technique is that it can be used at high speeds, including the transonic range. Model wings ...
A technique for the automatic, digital analysis of flight dynamic response data

A. P. Waterfall (1970)

A technique is described for using a digital computer for the extraction of aerodynamic force and moment derivatives from measurement of the motion of aircraft or aircraft models, following a disturbance from the trimmed ...
Temperature and pressure studies in the reservoir of a reflected-shock hypersonic tunnel

K. C. Lapworth; J. E. G. Townsend (1964)

Temperatures and pressures have been measured in the shock-heated gas upstream of the nozzle of a reflected-shock hypersonic tunnel. Temperatures were measured by spectrum-line reversal, using sodium D lines for some ...
The test performance of highly loaded turbine stages designed for high pressure ratio

I. H. Johnston; D. C. Dransfield (1959)

A blade design for a highly loaded two-stage turbine is described and the test performance of the turbine is presented. Some of the factors affecting the performance and matching of turbine blade rows operating at supersonic ...
Tests at high subsonic speeds on a 10 per cent thick pressure-plotting aerofoil of RAE 104 section

E. W. E. Rogers; C. J. Berry; R. F. Cash (1951)

1. Summary and Introduction.--A series of tests has been made in the National Physical Laboratory 20-in. x 8-in. High Speed Wind Tunnel on a two-dimensional pressure-plotting aerofoil of five inches chord and RAE 104 ...
Tests at subsonic and supersonic speeds on a slender cambered wing with fin, underwing engine nacelles and trailing-edge controls

D. Isaacs (1967)

The tests were made in the 8 ft x 8 ft wind tunnel at R.A.E. Bedford on a 1/36 scale model of a possible design for a supersonic transport aircraft. The wing camber was designed, using slender-wing theory, to have attached ...
Tests at transonic speeds on wings with wedge sections and sweep varying between 0 degree and 60 degrees

E. W. E. Rogers; C. J. Berry; V. G. Quincey (1961)

Tests have been made in the N.P.L. 18 in. by 14 in. High-Speed Tunnel at stream Mach numbers between 0.6 and 1.2 on two finite wings of identical planform and having single-wedge and double-wedge sections of 14% and 7% ...
Tests concerning novel designs of blades for axial compressors Part 1 blades designed for increased work at root and tip Part 2 blades designed to operate in a parabolic axial velocity distribution

S. J. Andrews; R. A. Jeffs; E. L. Hartley (1951)

Investigation of the flow between the blade rows in a research compressor with conventional Half-Vortex blades have shown a rapid stage-to,stage build-up of the annulus boundary layer. The axial velocity distribution under ...
Tests in the compressed air tunnel on the aerofoils NACA 0015 and NACA 0030 with and without split flap and on other aerofoils of various thicknesses with a split flap

R. Jones (1940)

To obtain information on the effect of thickness on the aerodynamic characteristics of aerofoils with and without a split flap. The following 4 ft. by 8 in. rectangular aerofoils were tested :- NACA 0015 and NACA 0030 with ...
Tests in the R.A.E. 10-ft x 7-ft high speed wind tunnel on drop tanks fitted to two swept-back wings Part 1 Comparison of under-wing and wing-tip installations Part 2 Comparison of various under-wing drop-tank arrangements

D. E. Hartley; A. B. Haines (1952)

The report describes tests made in the Royal Aircraft Establishment 10-ft × 7-ft High Speed Wind Tunnel on drop tanks, fitted to two wings, having the same plan-form with a sweepback of 40 deg and an aspect ratio of 3.5, ...
Tests in the Royal Aircraft Establishment 10-ft x 7-ft high-speed tunnel on 50-deg swept-back wings. Part I. Three of 7.5 per cent thickness. Part II. One of 7.5 per cent thickness with stall fences and leading-edge chord extension

A. B. Haines; C. W. Rhodes (1954)

Tests have been made in the Royal Aircraft Establishment 10-ft x 7-ft High-Speed Tunnel on three half-wings having a sweepback of about 50 deg on the quarter-chord line and 7.5 per cent thick sections. Two of the wings had ...
Tests of a griffith aerofoil in the 13 ft. x 9 ft. wind tunnel. Parts I. II, III and IV

E. J. Richards; W. S. Walker; J. R. Greening (1944)

PART I. Wind-tunnel Technique and Interim Note. PART II. Effect of Concavity on Drag. PART III. The Effects of Wide Slots and of Premature Transition to Turbulence. PART IV. Lift, Drag, Pitching Moments and Velocity ...
Tests of Contra-rotating Propellers of 2 7/8-ft. Diameter at Negative Pitch on a "Typhoon" Aircraft Model

R. C. Pankhurst; J. N. Veasey; J. R. Greening; Miss E. M. Love (1945)

The previous tests of a pair of contra-rotating two-bladed propellers have been extended to the propeller 'braking' condition by covering the range of pitch setting from 0 deg. to - 30 deg. at the 0.7 radius. Measurements ...
Tests of model propellers in the high speed tunnel thrust and torque measurements on a 2-blade, 6 per cent. thick, Clark Y section propeller

G. S. Hislop; J. Caldwell; M. Jones (1945)

High-speed wind tunnel tests of various model propellers were required as part ofa general research programme dealing with propellers for high-speed aircraft. A two-blade 4 ft 6 in diameter Clark Y section propeller of 6 ...

Now showing items 1115-1134 of 1313

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