Apparatus is described for the measurement of shock attenuation in channels of several configurations. A circular-bore channel, a square-bore channel and converging and diverging channels have been investigated. Measurements ...
A modified form of the approximate method developed by Kryloff and Bogoliuboff is derived and applied to particular cases with a large frequency dependence on amplitude. The results suggest that some relaxation of the ...
A method of calculating the fuel boiling losses, due to aerodynamic heating, from a supersonic aircraft with integral wing fuel tanks is devised and is applied to the Concord, assuming flight conditions of Mach 2.2 at 64000 ...
This paper collects together the flow patterns observed by an oil film (titanium oxide) technique over ten different Swept-back wings at high incidence and low Mach number in the Royal Aircraft Establishment 10-ft X 7-ft ...
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 ...
Harmonic and subharmonic solutions are determined numerically for the forced oscillations of a system governed by Duffing's equation, and the stability of these oscillations is discussed.
A delta-winged model, with 54.8-deg leading-edge sweep and a 6 per cent thick RAE 101 section, has been tested in the Royal Aeronautical Establishment (Bedford) 3-ft Wind Tunnel. The results of lift and pitching moment ...
Some of the more important practical implications to pilot's control, flight test analysis, and stability augmentor performance of classical longitudinal stability theory are discussed. The distinction between turns and ...