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Solutions for supersonic rotational flow around a corner using a new co-ordinate system

Published online by Cambridge University Press:  28 March 2006

T. C. Adamson
T. C. Adamson
Affiliation:
Department of Aerospace Engineering, The University of Michigan, Ann Arbor, Michigan
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Abstract

A co-ordinate system consisting of the left-running characteristics (α = const.) and the streamlines (ϕ = const.) is used. The governing equations are derived in terms of α and ϕ for a two-dimensional steady supersonic rotational inviscid flow of a perfect gas. The equations are applied to the problem of an initially parallel supersonic rotational flow which expands around a convex corner. The velocity of the incoming flow at the wall is considered to be either supersonic (case 1) or sonic (case 2). For each case, solutions uniformly valid in the region near the leading characteristic and in the region near the corner, are found for the Mach angle and flow deflexion angle in terms of their values on the leading characteristic and at the corner. In case 2, a transonic similarity solution is found and composite solutions are constructed for each region. Comparisons are made with existing exact numerical results.

Information

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 34 , Issue 4 , 23 December 1968, pp. 735 - 758
Copyright
© 1968 Cambridge University Press

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