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Oblique shock wave—turbulent boundary layer interaction with suction

Published online by Cambridge University Press:  04 July 2016

D. B. Lee and
R. Leblanc
D. B. Lee
Affiliation:
Centre d’Etudes Aérodynamiques et Thermiques, University of Poitiers, Poitiers, France
R. Leblanc
Affiliation:
Centre d’Etudes Aérodynamiques et Thermiques, University of Poitiers, Poitiers, France
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Abstract

The interaction of an incident oblique shock wave with the turbulent boundary layer with suction is investigated. Wall streamline and schlieren photograph visualisations as well as the pressure measurements on the wall are made. Boundary layer surveys with pressure probes and hot-wire probes are also done. The suction downstream of the interaction almost nullifies the shock reflection while the higher suction up and downstream of the interaction results in a reflection similar to that in inviscid flow.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 88 , Issue 879 , November 1984, pp. 416 - 427
Copyright
Copyright © Royal Aeronautical Society 1984 

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Footnotes

*

Present address: Korean Institute of Aeronautical Technology, Seoul.

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