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Reconsideration of oblique shock wave reflections in steady flows. Part 1. Experimental investigation

Published online by Cambridge University Press:  26 April 2006

A. Chpoun ,
D. Passerel ,
H. Li  and
G. Ben-Dor
A. Chpoun
Affiliation:
Laboratoire d'Aerothermique du CNRS, Meudon, France
D. Passerel
Affiliation:
Laboratoire d'Aerothermique du CNRS, Meudon, France
H. Li
Affiliation:
Pearlstone Center for Aeronautical Engineering Studies, Department of Mechanical Engineering, Ben-Gurion University of the Negev, Beer Sheva, Israel
G. Ben-Dor
Affiliation:
Pearlstone Center for Aeronautical Engineering Studies, Department of Mechanical Engineering, Ben-Gurion University of the Negev, Beer Sheva, Israel
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Abstract

The reflection of shock waves over straight reflecting surfaces in steady flows was investigated experimentally using the supersonic wind tunnel of Laboratoire d'Aerothermique du CNRS, Meudon, France. The results for a flow Mach number M0 = 4.96 contradict the state of the art regarding the regular [harr ] Mach reflection transition in steady flows. Not only was a hysteresis found to exist in this transition, but, unlike previous reports, regular reflection configurations were found to be stable in the dual-solution domain in which theoretically both regular and Mach reflection are possible.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 301 , 25 October 1995 , pp. 19 - 35
Copyright
© 1995 Cambridge University Press

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