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Heat transfer from a hypersonic turbulent boundary layer on a flat plate

Published online by Cambridge University Press:  29 March 2006

G. T. Coleman ,
C. Osborne  and
J. L. Stollery
G. T. Coleman
Affiliation:
Department of Aeronautics, Imperial College, London
C. Osborne
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 to a sharpedged flat plate inclined at various incidences to generate local Mach numbers from 3 to 9. The measurements have been compared with a number of theoretical estimates by plotting the Stanton number against the energy-thickness Reynolds number. The prediction giving the most reasonable agreement throughout the above Mach number range is that due to Fernholz (1971).

The values of the skin-friction coefficient derived from velocity profiles and Preston tube data are also given.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 60 , Issue 2 , 4 September 1973 , pp. 257 - 271
Copyright
© 1973 Cambridge University Press

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