Tests were required to be made on six kites over a greater range of wind speed than for previous large-tunnel tests. The kites used during the investigation were (A) 3-ft Cody kite Mk. II, (B) 3-ft reversed Cody or Dyco ...
This report shows that the application of classical flutter theory to the determination of wing flexural-torsional flutter speeds is considerably simplified by the omission of a term which is usually the very small difference ...
T. V. Somerville; R. R. Duddy; G. H. L. Buxton(1940)
Tests were made in the 24-ft Wind Tunnel during March and April, 1940, on the Whirlwind aircraft to find if simple modifications can be introduced which will decrease its drag. The drag analysis is not complete and is ...
By an arithmetical method, contours of constant Mach number have been determined in the contraction cone of a circular tunnel whose axial distribution of area was assumed to be the same as that in the Royal Aircraft ...
It was shown in Aeronautical Research Council Report No. 5455 that the accurate stress-function solution of certain two-dimensional problems of stress distribution may be replaced, with negligible error, by the approximate ...
This report gives the results of tests made in the Royal Aircraft Establishment 24-ft Wind Tunnel on the de Havilland propeller for the Aeronautical Research Council research programme initiated in 1943. The propeller was ...
It is demonstrated in this report that the 'steady stick force per g' as defined by Gates and Lyon in R. & M. 2027 is the best criterion for the measurement of manoeuvrability of an aircraft because: (a) practically, it ...
This report describes compression tests on 36 panels, made of D.T.D. 390 and D.T.D. 546. Each panel consisted of a flat skin reinforced with continuous corrugations, and the object of the test was to investigate the effect ...
A collection of surface pressure distributions measured on a number of axisymmetric forebodies at zero incidence and a Mach number of 3 is presented. Integrated pressure drags are compared with the theoretical drags of ...
Ignoring the dynamics of the automatic control loop hardware, the effects have been studied on rigid body mode stability, gust response and pilotVs control of aircraft in which relaxed longitudinal or directional stability ...
The investigation of aircraft handling characteristics at high angle of attack and high subsonic speeds is hampered by the lack of accurate data on aerodynamic derivatives. The development of a rig and method of test for ...
The Report describes a research programme undertaken at ARA in 1968-73. It represents the first attempt in the UK to design forecowl profiles for a podded engine nacelle of modern proportions, with the specific aim of ...
The objective of this work was to develop a method capable of producing reasonably accurate stage characteristics, in terms of mass flow, pressure ratio, work input and efficiency, for any centrifugal compressor with radial ...
The application of a long stroke isentropic free piston compressor as the energy source for an intermittent M = 6.85 hypersonic wind tunnel is described. The advantages of comparatively long running times of up to 0.5 s ...
Wind tunnel tests have been made to investigate the influence of the jets from several different nozzles on the pressure distribution on adjacent wing panels with supercritical profiles. In Part I, an existing unswept wing ...
Experiments suggest that the theory widely used to predict the transverse resonance frequencies in slotted tunnels is in error in the Mach number range from 0 to 0.5. One reason for the error is that the theory is based ...
Boundary layer developments have been measured for the flow downstream of an expansion corner when the boundary layer is disturbed by a shock wave striking the surface near the corner. It is found that most velocity profiles ...
A procedure is described for obtaining expansions in series of Chebyshev polynomials of the function [integration of e(to the minus i alpha u)du/(u squared plus 1) to the power of n + half] for all real alpha and all integer ...
In this report are collected together the calculated aerodynamic loadings due to incidence of a number of straight and swept-back wings. The calculations follow in the main the routine described previously in another report, ...