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Reflexion of an oblique shock wave by a turbulent boundary layer

Published online by Cambridge University Press:  29 March 2006

J. E. Green
J. E. Green
Affiliation:
Royal Aircraft Establishment, Bedford
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Abstract

Measurements are presented of the reflected wave field produced by a plane oblique shock wave impinging on a turbulent boundary layer at an initial Mach number of 2·5. The outgoing waves are either a single shock, with the same deflexion as the incident shock, or a shock of approximately 10° deflexion followed by a region of compression in which is embedded an expansion fan having the same turning as the incident shock. The transition between these two types of wave field was not studied, but it is fairly abrupt and appears to be closely linked to the onset of boundary-layer separation. The observed wave systems broadly agree with the suggestions of a number of previous workers, but not with a recent theoretical treatment. Surface-pressure measurements and oil flow photographs are used to determine the onset of separation, and from these it is found that the overall pressure rise associated with incipient separation is rather smaller than previous work would suggest.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 40 , Issue 1 , 14 January 1970 , pp. 81 - 95
Copyright
© 1970 Cambridge University Press

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References

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