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Turbulent hypersonic flow at a wedge-compression corner

Published online by Cambridge University Press:  29 March 2006

G.M. Elfstrom
G.M. Elfstrom
Affiliation:
Department of Aeronauties, Imperial College, London Present address: University of Tennessee Space Institure, Tulahorma.
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Abstract

A hypersonic gun tunnel has been used to investigate turbulent shock-boundary-layer interaction at a wedge-compression corner. The results extent the Mach number range of existing data, in particular of incipient separation.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 53 , Issue 1 , 9 May 1972 , pp. 113 - 127
Copyright
© 1972 Cambridge University Press

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References

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