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Supersonic Flow Past Wing-Body Combinations

Published online by Cambridge University Press:  07 June 2016

W. Chester
W. Chester*
Affiliation:
Department of Mathematics, University of Bristol
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Summary

The supersonic flow past a combination of a thin wing and a slender body of revolution is discussed by means of the linearised equation of motion. The exact equation is first established so that the linearised solution can be fed back and the order of the error terms calculated. The theory holds under quite general conditions which should be realised in practice.

The wing-body combination considered consists of a wing symmetrically situated on a pointed body of revolution and satisfying the following fairly general conditions. The wing leading edge is supersonic at the root, and the body is approximately cylindrical downstream of the leading edge. The body radius is of an order larger than the wing thickness, but is small compared with the chord or span of the wing.

It is found that if the wing and body are at the same incidence, and the aspect ratio of the wing is greater than 2 (M2-1)-½, where M is the main stream Mach number, the lift is equivalent to that of the complete wing when isolated. If the wing only is at incidence then the lift is equivalent to that of the part of the wing lying outside the body.

The presence of the body has a more significant effect on the drag. If, for example, the body is an infinite cylinder of radius a, and the wing is rectangular with aspect ratio greater than 2(M2-1)-½, then the drag of the wing is decreased by a factor (1-2a/b), where 2b is the span of the wing.

When these conditions do not hold the results are not quite so simple but are by no means complicated.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 4 , Issue 3 , August 1953, pp. 287 - 314
Copyright
Copyright © Royal Aeronautical Society. 1953

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