Flow photographs and detailed pressure distributions for a 4 per cent thick circular-arc biconvex aerofoil at high subsonic speeds and high incidences have been analysed and the divergence boundary (defining the onset of ...
The area-rule, moment of area-rule and transfer-rule methods for estimating the wave drag Of wing-body combinations are discussed. It is pointed out that the moment of area rule and the transfer rule are different forms ...
The equations of motion of the helicopter are presented and reduced to non-dimensional form. The force and moment derivatives for the single-rotor helicopter (including tailplane if required) are given as simple formulae ...
This report considers the loss of flexural rigidity of a thin wing due to the presence of middle-surface stresses resulting from aerodynamic heating. The spanwise properties of the wing are assumed constant but the wing ...
A description is given of an arithmetical method for obtaining solutions for steady incompressible viscous flow at low Reynolds numbers in the form of expansions in powers of the Reynolds numbers. The method has been used ...
This report describes tests on a single compressor stage with circumferentially non-uniform inlet conditions. The stage was a model of the first stage of a typical modern aircraft-engine compressor, and the tests were ...
A series of tests Was undertaken on a simple, two-dimensional, variable Mach-number effuser, or nozzle, designed for the range of supersonic flows up to Mach number 3.0. The performance of the nozzle was assessed from the ...
Camber and twist is applied to the problem of reducing the drag due to incidence, of thin triangular or swept-back wings, at supersonic speeds, with subsonic leading edges and supersonic or sonic trailing edges. Two cases ...
Methods recently developed for estimating distributions and intensities of sonic bangs are described. They are applied to several interesting flight manoeuvres and the results discussed in detail. The effect on sonic-bang ...
Direct-shadow and schlieren photographs and pressure distributions of the flow past a two-dimensional 4 per cent thick biconvex aerofoil for a limited range of incidences at Mach numbers of 1.40 and 1.63 are presented. ...
Tests have been made at Mach numbers up to 0.93 in the Royal Aircraft Establishment 10 ft X 7 ft High Speed Wind Tunnel to examine how the longitudinal characteristics of a fighter-type aircraft are affected by the ...
Axially-symmetrical, supersonic, fully-expanded jets of diameter about 0.75 in. and of Mach number 1.40 issuing into an atmosphere at rest were investigated by schlieren and shadow photography and by pressure traversing. ...
Below is given a list of the Reports and Memoranda published by the Aeronautical Research Council. The reference numbers other than the R. & M. numbers are not consecutive, as many reports are confidential to the Council ...