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 ...

Several methods are available for the calculation of the compressible turbulent boundary-layer. The earlier methods of Tucker (1951) and Young (1953) involve numerical integration, while the more recent methods of Englert ...

A description is given of apparatus developed at the Royal Aircraft Establishment for the study of the impact between a liquid drop and a surface moving at speeds up to 3,500 ft/sec. Some results obtained are briefly ...

Observations made in the viscous sub-layer of turbulent shear flows with small surface pitot-tubes and hot wires show that such instruments give accurate values of boundaryiayer skin friction, at least in zero pressure ...

On the assumption that the/tow normal to the external streamlines is small compared with that along the external streamlines it is shown that the streamwise momentum equation, the energy equation and the equation of ...