The problem of calculating the response of an aircraft in rolling manoeuvres when the mass distribution of the aircraft is such that the inertia terms in the equations of motion effect a cross-coupling of the usual lateral ...

The present position of the theory of supersonic turbulent base flow is reviewed and arguments are put forward which suggest that the theory of Korst and others is incorrect in certain respects. The analysis of two-dimensional ...

Two wings may be said to have equivalent pressure distributions if the distribution of Mn, the component of surface Mach number normal to the local isobars, is the same in both cases. A simple approximate method is given ...

The position of the breakdown of the tightly rolled leading-edge vortex was observed Using a smoke technique. The breakdown point moved forward with increasing incidence, and reached a point above the trailing edge at an ...

Calculations have been made of the induced drag of flapped elliptic wings covering a range of aspect ratios from about 4 to about 12, a range Of flap spans from 0.2 to 1.0 of the wing span, and a range of flap cut-outs ...

Approximate expressions for the generalised airforces acting on a rectangular wing of low aspect ratio oscillating harmonically in sonic flow at low frequencies are derived in this paper. The modes of oscillation considered ...

The routine testing of aircraft-type compressors--in the main, axial-flow, multi-stage compressors--requires a compromise between research accuracy and the practical considerations. This test code is the outcome of a survey ...

This report describes the flight tests made at the Royal Aircraft Establishment on the Rolls-Royce Flying Bedstead to investigate the stability and control problems of a hovering jet-lift aircraft. Tests made with varying ...

The paper gives a theory of vortex flow in turbo-machines in which the basic assumption is made that the axial-velocity profiles always belong to a family governed by a single parameter, λ. This parameter is a measure of ...

Balance measurements of lift, pitching moment and thrust on an aspect-ratio 6 half-model wing and body in the N.P.L. 13 ft × 9 ft Wind Tunnel are discussed, and compared with theoretical estimates. The experimental ...