Aeronautical Research Council (1945-1979): Recent submissions

Now showing items 41-60 of 2706

Low-speed wind-tunnel tests on a 1/8th scale model of the Handley-Page HP.115

P. B. E. Engler; G. F. Moss (1965)

A series of tunnel tests was made on a slender wing design to provide a basis for the flight-tunnel comparison of data and to give general wind-tunnel support for the flight research work on the aeroplane. The interim ...
The calculation of the spanwise loading of sweptback wings with flaps or all-moving tips at subsonic speeds

G. G. Brebner; D. A. Lemaire (1955)

The results of some electric tank tests by Duquenne and Grandjean on wings of 45 deg sweepback with trailing edge flaps have been analysed to provide the basis for a method of calculating the spanwise loading. The analysis ...
Wind-tunnel tests on the spoiling effects of engine cooling gills on radial air-cooled installations on a wing

J. Seddon; J. A. Kirk (1942)

Information was required on the spoiling drag associated with opening cooling gills on radial air-cooled engine installations on a wing. Maximum lift, drag up to high CL, and cooling flow were measured on a 1/12 scale model ...
The design-point performance of model internal-expansion propelling nozzles with area ratios up to 4

M. V. Herbert; D. L. Martlew; R. A. Pinker (1963)

The construction of a new dry air thrust rig is described, for testing model propelling nozzles in quiescent air, and its pretensions to accuracy are examined. Use has been made of certain types of convergent nozzle as a ...
Some exact calculations of the lift and drag produced by a wedge in supersonic flow, either directly or by interference

P. L. Roe (1964)

Exact inviscid theory is applied to a simple lifting configuration consisting of a wedge beneath a plane wing, both the wedge and the wing being terminated by a trailing edge which lies along a Mach cone. The efficiency ...
Some flight measurements of crosswind landings on a small delta aircraft (Avro 707A)

K. J. Staples (1965)

Pilots' control movements and the accuracy of touchdown have been analysed for two distinct crosswind landing techniques. The sideslipping technique gave generally better accuracy at touchdown. On the other hand, the ...
Physical characteristics of the sonic bangs and other events at Exercise Westminster

D. R. B. Webb; C. H. E. Warren (1965)

Exercise Westminster was a demonstration of sonic bangs, together with some explosive bangs and flyovers by a jet aircraft, staged for an invited audience. This Report describes how the Exercise was conducted from the ...
Experiments at M0 = 4.03 on two families of pressure-plotting wing-and-half-cone combinations

E. W. E. Rogers; J. L. Attridge; Miss A. G. J. Macdonald; J. Callinan (1964)

Tests have been made at a Mach number of 4.03 and Reynolds number of 3.4 million on two families of models, consisting of delta wings with underslung half-Cone bodies. The wing sweepback angles were 75° and 80°, and the ...
The calculation of the warp to produce a given load and the pressures due to a given thickness on thin slender wings in supersonic flow

J. H. B. Smith; J. A. Beasley; Diana Short; F. Walkden (1965)

According to the linearized theory of supersonic flow, both the local slope of the mean surface of a wing producing a specified distribution of lift and the pressure on a wing due to a specified distribution of volume are ...
Fatigue test results and analysis of 42 piston provost wings

H. E. Parish (1965)

The safe fatigue life of the Piston Provost was established by full-scale, programmed load, fatigue tests, the load spectrum being collected from 'in service' records. Forty 'life-expired' wings and an appropriate number ...
Computer calculations of relaxation regions and equilibrium conditions for shock waves with tables for CO2 and N2O

T. Rees (1965)

Johannesen has discussed a Rayleigh-line method for the analysis of vibrational relaxation regions in shock waves. In this method the flow of the real gas in the relaxation region is treated as the flow of an ideal gas ...
Wind Tunnel Tests on a Streamlined Fan-Lift Nacelle Part I. Tests on Nacelle Alone and with Wings or Underfins Fitted Part II. The effect of Forward Speed on the Lift Produced by a Lifting Fan and its Inlet

J. E. Hackett (1965)

Part I describes tests on a streamlined body with a lifting fan mounted normally to its axis. Most of the tests were made in the 5 ft x 4 ft windtunnel at Imperial College, and others in the No. 1 11½ ft x 8½ ft tunnel at ...
The effects of base bleed on plug nozzles

J. Reid (1965)

This is an experimental comparison Of two axi-symmetric, isentropic plug nozzles. In one of these (Model No. 1) the afterbody is cylindrical and a secondary flow is bled into the annular base. The other (Model No. 2) has ...
A numerical method for solving the equations for a vortex core

M. G. Hall (1965)

A method is presented for calculating steady axially symmetric spiralling motions of an incompressible fluid at large Reynolds numbers. By making approximations of the boundary-layer type the Navier-Stokes equations are ...
A discussion of two-dimensional turbulent base flows

J. F. Nash (1965)

The paper presents a review of recent experimental and theoretical research on two-dimensional base flows. The main object is to illustrate the extent to which the basic properties of the flow are understood in each of the ...
Feed-back accelerometer circuits with a velocity output

R. H. Evans; G. G. Haigh (1964)

Circuits are suggested for modifying the feed-back loop of an accelerometer so that the output voltage is proportional to velocity, that is, an integrating process is incorporated within the loop. The main advantage is ...
A new two-parameter family of mean velocity profiles for incompressible turbulent boundary layers on smooth walls

B. G. J. Thompson (1965)

The combination of two universal functions, representing the effects of the wall and of the 'intermittency' in the other region, has been used to construct a new profile family. Comparisons with measured profiles are very ...
Experiments concerning the effect of trailing-edge thickness on blade loss and turbine stage efficiency

I. H. Johnston; D. C. Dransfield; D. J. Fullbrook (1964)

Theoretical assessments of the influence of trailing-edge thickness on turbine blade loss coefficients are reviewed and compared with the results of a cascade tunnel investigation. Tests on a single-stage turbine indicate ...
A review of the problem of choosing a climb technique, with proposals for a new climb technique for high performance aircraft

K. J. Lush (1948)

The climb techniques at present used on modern aircraft entail quite high true air speeds and high kinetic energies. It was desired to investigate the effect of kinetic energy variation with height, which is ignored in ...
The development of injector units for jet-lift engine simulation on low-speed-tunnel models

M. N. Wood; J. B. W. Howard (1965)

Small-scale injector units have been developed for providing the engine nacelles of V/STOL models, with both intake and exit flows. The primary energy supply was cold compressed air at pressure ratios up to 4:1. With the ...

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