PART I. Tests were made in the Royal Aircraft Establishment No. 19 (18 in. x 18 in.) supersonic wind tunnel to measure the overall normal and side forces, rolling, pitching and yawing moments on a typical canard aircraft ...

This Report describes an experimental investigation of the factors affecting the base flow and jet structure behind a cylindrical after-body with a central nozzle. Seven interchangeable nozzles were tested. Six of these ...

Minimum values of the zero-lift wave drag of slender wings with certain fixed properties have been calculated by slender-body theory. The cross-sectional area distributions of the wings are taken to be polynomials and the ...

The classical theory of wind-tunnel interference is extended to cover interference on the effectiveness of a full-span jet flap issuing from the trailing edge of a high aspect ratio unswept wing. It is shown that, for small ...

Under review

Formulae for calculating the-gradients and ordinates of the camber surfaces of swept-back wings of arbitrary plan-form with subsonic leading edges, and specified load distribution, are given, including those which have ...

Summary. Wind-tunnel tests have been made at a Mach number of 2.92 to measure the effect of humidity on laminar recovery temperature on a cone. Its effect is to increase the recovery temperature above that obtained with ...

Note.--All papers discussed by the Aeronautical Research Council and recommended by them for external publication after 1st April, 1932, have been published in abstract only in the Reports and Memoranda Series. CONTENTS. ...

An account is given of a theoretical flutter investigation in connection with an accident to a Sea Venom aircraft. The investigation covers both symmetric and antisymmetric flutter of the tailplane-elevator-tab system. The ...

The results of force measurements and surface oil flow studies on a wing-body combination with an unswept wing of aspect ratio 3.5, taper ratio 0.5, and a 4 per cent biconvex section, are analysed. The tests were made at ...