Aeronautical Research Council: Recent submissions

Now showing items 261-280 of 2786

Some applications of 'not-so-slender' wing theory to wings with curved leading edges

L. C. Squire (1960)

An extension of slender-wing theory, introduced by Adams and Sears, has been applied to some problems concerned with the properties of slender, lifting, wings with curved leading edges at supersonic speeds. Two particular ...
Part I The Flow Pattern on a Tapered Sweptback Wing at Math Numbers between 0.6 and 1.6 Part II Experiments with a Tapered Sweptback Wing of Warren I 2 Planform at Mach Numbers between 0.6 and 1.6

I. M. Hall; E. W. E. Rogers (1960)

PART I. The development of the flow pattern on a swept wing with incidence and stream Mach number is described. The wing, of aspect ratio 2.828, taper ratio 0.333 and leading-edge sweep 53.5 deg, was tested at Mach numbers ...
A theoretical investigation of the longitudinal stability, control and response characteristics of jet-flap aircraft Parts 1 and 2

A. S. Taylor (1960)

Foreword (1961). Parts I and II of this R. & M. were written as separate Reports in 1958 and 1960. They deal with two stages of an exploratory investigation into the stability, control and response characteristics of ...
The performance of supersonic turbine nozzles

B. S. Stratford; G. E. Sansome (1959)

An investigation has been conducted at the National Gas Turbine Establishment into the performance of turbines having high pressure ratios per stage. The present Report discusses the mode of operation of supersonic nozzles ...
A study of the effect of leading-edge modifications on the flow over a 50-deg sweptback wing at transonic speeds

E. W. E. Rogers; C. J. Berry; J. E. G. Townsend (1960)

An investigation has been made in the N.P.L. 18 in. x 14 in. Tunnel of the effects of leading-edge modifications on the flow and forces on an untapered wing of 50 deg leading-edge sweep, at stream Mach numbers between 0.60 ...
Concept of complex stiffness applied to problems of oscillations with viscous and hysteretic damping

S. Neumark (1957)

The concept of complex stiffness in problems of oscillations with viscous, or structural (hysteretic) damping is often used in a wrong way, leading to erroneous solutions. It is shown in the Paper that correct expressions ...
The effect of temperature variations in the plane and through the thickness of a circular lenticular plate

E. H. Mansfield (1961)

This Paper presents a large-deflexion analysis of a thin circular lenticular plate whose temperature varies parabolically in its plane and linearly through its thickness. The analysis embraces the buckled, as well as ...
Effects of wing stiffness and inertia changes on the modes and frequencies of a model delta aircraft

D. R. B. Webb (1959)

Resonance tests were made on a model delta aircraft to investigate the effect of stiffness changes of the leading- and trailing-edge spars on the frequencies and modes of vibration of the model. The results showed that, ...
An approximate solution of two flat plate boundary layer problems

E. J. Watson; J. H. Preston (1946)

The method presented here for obtaining an approximate solution of the laminar boundary-layer equations is based on the iteration process of Piercy and Preston. It leads to a simple analytical approximation of good accuracy ...
Stresses produced in an infinite elastic plate by the application of loads travelling with uniform velocity along the bounding surfaces

L. S. D. Morley (1961)

Using Fourier integrals, a quasi-steady solution is obtained to the title problem where the direction of motion, shape and size of the loading distribution do not vary with time. The loads are, moreover, assumed equally ...
Wind tunnel tests and theoretical investigations on the effect of a localised mass on the flutter of a delta wing with fixed root

G. F. Donno (1959)

Summary.--Wind tunnel tests and theoretical investigations have been carried out to study the effect of a localised mass on the flutter characteristics of a delta wing. The experimental work covered a wide range of spanwise ...
On the flow in a reflected-shock tunnel

D. W. Holder; D. L. Schultz (1960)

The performance of a shock tunnel operated by the reflected-shock technique is examined theoretically neglecting viscous effects and high-temperature real-gas effects. Particular attention is given to disturbances to the ...
Measurements of lift and ground interference on a lifting-fan wing at zero forward speed

N. Gregory; W. S. Walker (1958)

Measurements were made at zero forward speed of the forces acting on a lifting-fan wing system of hexagonal planform. The diameter of the wing was reduced in the course of the experiment from five times to twice the diameter ...
The R.A.E. 4-ft x 3-ft experimental low-turbulence wind tunnel. Part IV. Further turbulence measurements

H. Schuh (1953)

Further measurements of turbulence in the working section are given with 2 and 3 screens in the bulge. The extended region of high intensity turbulence near the walls of the working section, which was observed with 9 screens ...
A proposed apparatus for measuring oscillatory aerodynamic derivatives

L. H. G. Sterne (1959)

This Report describes the principles to be used in designing an apparatus, including half-model of an aircraft, for measuring longitudinal oscillatory aerodynamic derivatives in the R.A.E. High Speed Tunnel. The model is ...
Interactions between normal shock waves and turbulent boundary layers

G. E. Gadd (1961)

A theory, involving a simple new method for turbulent boundary layers, is presented for interactions between normal shocks and turbulent boundary layers on flat surfaces. Experiments in a pipe confirm the theory's general ...
No. 2, 11 1/2-ft wind-tunnel tests of a small span, small chord double aileron for use as a lateral control on a high-lift aircraft

A. D. Young; W. S. D. Marshall (1946)

Tests were made on a 1/2.25 scale model of a half wing of the Master. The span of the aileron was 0.22s and the chords were 0.2c and 0.15c; the aileron was fitted with a balance tab of 0.05c chord. Measurements were made ...
A narrow-band spectral analyser for random waveforms

D. S. Whitehead (1960)

The Report describes an analyser which was developed for finding the power spectra of waveforms derived from vibrating axial compressor blades due to random excitation. The bandwidth of the instrument goes down to about ...
Measurements of the direct pitching-moment derivatives for two-dimensional flow at subsonic and supersonic speeds and for a wing of aspect ratio 4 at subsonic speeds

J. B. Bratt; W. G. Raymer; J. E. G. Townsend (1959)

Apparatus based on a self-excitation technique has been developed for the measurement of direct pitching-moment derivatives at high speeds, and has proved to function satisfactorily. Measurements have been made at subsonic ...
Wind-tunnel tests on the effects of an added mass on the flutter of a model delta wing part 1 fixed root flutter tests part 2 anti-symmetric flutter tests part 3 symmetric flutter tests

H. Hall; W. A. Coles (1958)

Summary. A comprehensive investigation of the fixed root, anti-symmetric and symmetric flutter characteristics of a model delta wing carrying an added mass has been made. The parameters that were varied in the tests were ...

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