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Heat transfer from hypersonic turbulent flow at a wedge compression corner

Published online by Cambridge University Press:  29 March 2006

G. T. Coleman  and
J. L. Stollery
G. T. Coleman
Affiliation:
Department of Aeronautics, Imperial College, London
J. L. Stollery
Affiliation:
Department of Aeronautics, Imperial College, London
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Abstract

A hypersonic gun tunnel has been used to measure the heat-transfer-rate distribution over a compression corner under turbulent boundary-layer conditions. Attached, incipient and separated flows are considered. The results are compared with other experimental data and with the predictions of a simple theory.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 56 , Issue 4 , 28 December 1972 , pp. 741 - 752
Copyright
© 1972 Cambridge University Press

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