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An experimental study of the interaction between a glancing shock wave and a turbulent boundary layer

Published online by Cambridge University Press:  20 April 2006

Hayao Kubota  and
John L. Stollery
Hayao Kubota
Affiliation:
Technical Research and Development Institute, Japan Defense Agency, Tokyo, Japan
John L. Stollery
Affiliation:
College of Aeronautics, Cranfield Institute of Technology, Bedford, England
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Abstract

The glancing interaction between an oblique shock wave and a turbulent boundary layer has been studied experimentally using a variable-incidence wedge mounted from the side wall of a supersonic wind tunnel. The Mach number was 2·3 and the Reynolds number 5 × 104, based on the 99·5 % thickness of the boundary layer just upstream of the interaction region. The study includes oil flow pictures, vapour and smoke-screen photographs, wall-pressure distributions and local heat-transfer measurements. The results suggest that the complicated interaction region involves two viscous layers: an induced layer formed from fluid initially in the boundary layer growing along the wedge surface near the root, and the thick turbulent layer on the tunnel side wall. The mutual interference between these layers is described, separation is defined and a discussion of incipient separation is included.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 116 , March 1982 , pp. 431 - 458
Copyright
© 1982 Cambridge University Press

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