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Boundary-layer drag in three-dimensional supersonic flow

Published online by Cambridge University Press:  28 March 2006

J. C. Cooke
J. C. Cooke
Affiliation:
Royal Aircraft Establishment, Farnborough
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Abstract

A general theorem for drag is given according to which the boundary-layer drag of a body is equal to the inviscid drag of the displacement surface together with a term which is given as an integral involving the ‘streamwise’ momentum and displacement thicknesses taken round the trailing edge. A less accurate result for thin slender wings is that the boundary-layer drag is equal to the line integral $\rho _\infty U^2_\infty \int \Theta d \sigma$ taken round the trailing edge, where Θ is the streamwise momentum thickness. This result leads to the possibility of finding boundary-layer drag by means of a traverse round the trailing edge. The extension of the results to wings with swept trailing edges is also given.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 17 , Issue 1 , September 1963 , pp. 61 - 74
Copyright
© 1963 Cambridge University Press

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