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Boundary-layer drag in three-dimensional supersonic flow
Published online by Cambridge University Press: 28 March 2006
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.
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- © 1963 Cambridge University Press
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