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The shock-shock interaction between two similar wedges was investigated in the Mach number range of 2–2.8 in a continuously varying Mach number wind tunnel. The average dM/dt of the present study is 1.25. The wedge angle was chosen to be 17.5 \(^\circ \) to observe hysteresis as predicted by theory. The flow transitions from unstart of the model \(\rightarrow \) strong Mach interaction \(\rightarrow \) weak Mach interaction \(\rightarrow \) regular interaction for increasing Mach number cases and vice versa for decreasing Mach number cases. The moving strong shock solution was observed during the starting/unstarting of the model. This phenomenon was observed for the first time here. The hysteresis was not resolvable with the current imaging resolution.

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Investigation of Shock–Shock Interaction in Variable Mach Number Flow

  • 会议论文

  • 发表日期：

    2025年

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  • V. Vijayakrishnan,
  • Madhura Narayana Sabhahit,
  • T. M. Muruganandam

摘要

The shock-shock interaction between two similar wedges was investigated in the Mach number range of 2–2.8 in a continuously varying Mach number wind tunnel. The average dM/dt of the present study is 1.25. The wedge angle was chosen to be 17.5 \(^\circ \) to observe hysteresis as predicted by theory. The flow transitions from unstart of the model \(\rightarrow \) strong Mach interaction \(\rightarrow \) weak Mach interaction \(\rightarrow \) regular interaction for increasing Mach number cases and vice versa for decreasing Mach number cases. The moving strong shock solution was observed during the starting/unstarting of the model. This phenomenon was observed for the first time here. The hysteresis was not resolvable with the current imaging resolution.