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Boundary Layer Transition Measurements Using a Surface Hot Film Downstream of Distributed Roughness at Mach Numbers from 1·3 to 4·0

Published online by Cambridge University Press:  04 July 2016

D. G. Mabey
D. G. Mabey*
Affiliation:
Royal Aircraft Establishment, Bedford
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Summary

A surface hot film was used as a boundary layer transition indicator on wind tunnel models at Ifiach numbers from 1·3 to 4·0. The results illustrate the difficulty of fixing transition with distributed roughness on small models at supersonic speeds.

Type
Research Article
Information
The Aeronautical Journal , Volume 69 , Issue 650 , February 1965 , pp. 96 - 100
Copyright
Copyright © Royal Aeronautical Society 1965

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References

1.Mabey, D. G. ARC 24,844. ARC CP 738, 1963.Google Scholar
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4.Potter, J. L. and Whitfield, J. D.Journal of Fluid Mechanics, Vol. 12, p 501, 1962.Google Scholar
5.Van Driest, E. R. and Blumer, C. B.Journal of the Aerospace Sciences, Vol. 29, p 909, 1962.CrossRefGoogle Scholar