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Transition of shock reflection with downstream expansion fan interference

Published online by Cambridge University Press:  12 March 2025

Yiwen He Open the ORCID record for Yiwen He [Opens in a new window]  and
Aiming Shi Open the ORCID record for Aiming Shi [Opens in a new window]
Yiwen He
Affiliation:
School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, PR China
Aiming Shi*
Affiliation:
School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, PR China National Key Laboratory of Aircraft Configuration Design, Xi’an 710072, PR China
*
Corresponding author: Aiming Shi, sam@nwpu.edu.cn
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Abstract

In this paper, the reflection of shock waves with downstream expansion fan interference in two-dimensional, inviscid flow is investigated, including steady Mach reflection (MR) and the unsteady transition process from regular reflection (RR) to MR. A threshold for the configuration based on non-dimensional wedge length is proposed. The analytical model for the steady MR and RR$\rightarrow$MR transition process is established based on the classical shock and expansion wave relations, whose prediction agrees well with results obtained through inviscid numerical simulation. It is found that the expansion fan interference significantly influences the steady flow patterns, especially the height of the Mach stem and the shape of the slip line. The interaction accelerates the formation of the sonic throat, stabilizing the flow structure rapidly, and results in generally small Mach stem heights. The exposure of the triple point to the expansion fan eliminates the inflection point on the slip line, whose slope increases smoothly. The interaction further affects the time evolution of the Mach stem during the multiple-interaction stage of the RR$\rightarrow$MR transition process. It appears that the modifications come from the curvature of the incident shock brought by the wave interference. During the multiple-interaction stage, the triple point moves upstream along the curved incident shock, where the incident shock angle changes according to the curvature, resulting in the variation of the evolution velocity.

JFM classification

Compressible Flows: Gas dynamics Compressible Flows: Shock waves Compressible Flows: Supersonic flow
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 1007 , 25 March 2025 , A5
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Copyright
© The Author(s), 2025. Published by Cambridge University Press

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