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

D. D. Clark (1951)

In M.R.P. 527 Shellard has summarised the evidence indicating that a variation takes place in the speed-correction coefficient of aircraft thermometers both with altitude and, in One particular case, with air speed. He ...

Low-speed experiments on the wake characteristics of flat plates normal to an air stream

R. Fail; J. A. Lawford; R. C. W. Eyre (1957)

Experiments on isolated fiat plates perpendicular to the wind are described. It is shown that the effects of aspect ratio on drag, base pressure and flow pattern are small up to A = 10. All of these rectangular plates shed ...

Some experiments on the resistance of metals to fatigue under combined stresses

H. J. Gough; H. V. Pollard; W. J. Clenshaw (1951)

The basic object of the investigation was an experimental study of the fatigue resistance of metals to combined flexural and torsional stresses to which many engineering components; particularly crankshafts, are subjected ...

Experimental observation of vortices in wing-body junctions

A. Stanbrook (1957)

Tests have been made on various wing-body combinations to investigate the nature of the flow in the junction. It was found that vortices are formed due to separation of the boundary layer on the body in the flow towards ...

The theoretical evaluation of the downwash behind jet-flapped wings

A. J. Ross (1958)

The dovwnwash behind jet-flapped wings of infinite and finite span has been evaluated, using the solutions given by Spence and Maskell for the flow in two and three dimensions respectively. The wing incidence and jet ...

A theory of the separated flow from the curved leading edge of a slender wing

J. H. B. Smith (1957)

The simple model used by Brown and Michael to represent the flow past a slender delta wing with leading edge separation, is extended to treat wings which have pointed apexes, curved leading edges and straight, unswept ...

Helicopter behaviour in the vortex-ring conditions

W. Stewart (1951)

A region of roughness, associated with the airflow conditions of the vortex-ring state, occurs when a helicopter is operating in vertical or near vertical descents in the range of about 500 and 1,500 ft/min. The turbulent ...

The influence of aerodynamic heating on the flexural rigidity of a thin wing

E. H. Mansfield (1957)

This report considers the loss of flexural rigidity of a thin wing due to the presence of middle-surface stresses resulting from aerodynamic heating. The spanwise properties of the wing are assumed constant but the wing ...

A frost-point hygrometer for supersonic wind tunnels

D. Beastall; A. Winyard (1951)

This report describes a frost-point hygrometer suitable for measuring the water-vapour content of the air in supersonic wind tunnels at any stagnation pressure within their present range of operatiom It uses CO2 as a coolant ...

Air-cooling methods for gas-turbine combustion systems

F. J. Bayley (1951)

This paper presents an account of the whole of the work which has been done at the National Gas Turbine Establishment on the problem of air cooling gas-turbine combustion systems. Each of the different methods, of wall ...

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

E. F. Relf (1952)

In studying anct comparing various theories for the determination of the distribution of loading on wings, Garner has given values for the lift slope of several families of swept-back and delta wings deduced from several ...

Some effects of shock-induced separation of turbulent boundary layers in transonic flow past aerofoils

H. H. Pearcey (1955)

The effects of shock-induced separation of turbulent boundary layers on two-dimensional aerofoils are introduced by considering the development of the surface-pressure distribution and flow pattern as the free-stream speed ...

Methods for estimating distributions and intensities of sonic bangs

D. G. Randall (1957)

Methods recently developed for estimating distributions and intensities of sonic bangs are described. They are applied to several interesting flight manoeuvres and the results discussed in detail. The effect on sonic-bang ...

The Ideal Drag Due to a Shock Wave. Parts I and II

C. N. H. Lock (1945)

Part 1. The subject of the present note is the increase of the drag of an aerofoil which arises from the presence of limited shock waves when the forward speed lies between the so-called shock stalling speed and the velocity ...

Aerodynamic Characteristics in the Approach, Superfine and Negative Pitch Ranges of Two Four-Bladed Propellers with N.A.C.A. Series 16 Blade Sections.

Technical Staffs of de Havilland Propellers; Limited; Rotol; Limited. (1957)

Tests were conducted on two similar full-scale propellers in tim 24-ft Wind Tunnel at the Royal Aircraft Establishment by representatives of Rotol, Ltd. and de Havilland Propellers, Ltd. to measure the aerodynamic ...

The R.A.E. electronic simulator for flutter investigations in six degrees of freedom or less

F. Smith; W. D. T. Hicks (1953)

This report describes, the design and construction of an electronic simulator for flutter investigations in any number of degrees of freedom not exceeding six. Tile principles of the simulation are discussed, and the actual ...

Aspect-ratio effects on compressor cascade blade flutter

D. A. Kilpatrick; R. A. Burrows (1956)

This report gives the results of cascade tests on blades of aspect ratio varying from 3.0 to 1.5, with particular reference to stalling flutter. It is concluded that the influence of aspect ratio on stalling flutter cannot ...

Longitudinal stability and control of the single-rotor helicopter

A. R. S. Bramwell (1957)

The equations of motion of the helicopter are presented and reduced to non-dimensional form. The force and moment derivatives for the single-rotor helicopter (including tailplane if required) are given as simple formulae ...

Experiments with a two-dimensional aerofoil designed to be free from turbulent boundary-layer separation at small angles of incidence for all mach numbers

D. W. Holder; R. F. Cash (1957)

The present investigation was designed primarily to check the validity of a simple method which had been suggested for designing an aerofoil section on which, for a limited range of incidence, turbulent boundary-layer ...

The shape of the centre part of a swept-back wing with a required load distribution

J. Weber (1957)

A method is developed for designing the centre portion of a cambered and twisted swept-back wing to have the same chordwise load distribution at all spanwise stations. For this purpose the downwash field induced by a doublet ...

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