The compressible turbulent boundary layer on a flat plate with air injection has been investigated experimentally. Boundary-layer developments were measured at Mach numbers of 2.5 and 3.5 for the case of zero injection and ...
Three cellulose-nitrate model wings, identical except I0r rib flexibility, have been tested under conditions reproducing typical engine loads. Stress distributions have been found experimentally by means of electrical ...
This report contains an account of some experiments on the effect of concentrated masses (representing wing engines, etc.) on the flutter characteristics of a model cantilever wing. Flutter critical speeds and frequencies ...
Measurements of lift, drag and pitching moment have been made on five delta wing models to investigate the effects of thickness on the subsonic longitudinal characteristics of the 70 deg delta planform. For four of the ...
A wind-tunnel investigation of the effects of structural deformation on the pressure distributions round a tapered wing, with 44-deg leading-edge sweepback, has been carried out over a range of deformations at a Reynolds ...
Experiments have been made to determine the flow conditions through a helicopter rotor in forward flight using the smoke filament technique. This method consisted of flying the helicopter behind an aircraft from which smoke ...
The present research programme of the National Physical Laboratory is concerned with the influence exerted on model forces and surface pressures by the thick, laminar boundary layers characteristic of rarefied, near-continuum ...
A review of the literature on the subject of normal reflection of shock waves at the end of a shock tube is given and indicates that, although many of the phenomena which influence the motion of the reflected shock wave ...
An experimental investigation of one of the pair of vortices, produced above a delta wing at an incidence of 14.9 deg, has been made by means of a five-tube yawmeter head. Traverses through the axis of the vortex, at three ...
The lift, drag and pitching moment on five symmetrical slender-wing models with sharp edges and aspect ratios of 1.28 and 1.46 have been measured at low subsonic speed. Four of the models had a gothic planform and one a ...
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 ...