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<p>Results of numerical simulations of interaction of a supersonic boundary layer on a flat plate with an oblique shock wave generated by a thin wedge aligned at a right angle to the plate surface are reported. The problem is solved by means of combining a CFD code based on solving the Reynolds-averaged Navier–Stokes equations with the LOTRAN 3.0 software package based on the <i>e</i><sup><i>N</i></sup>-method. Specific features of the flow structure with primary and secondary separation regions are identified. It is shown that the shock-induced pressure gradient leads to the development of Tollmien-Schlichting instability waves and crossflow vortex instability.</p>

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Structure and stability of a supersonic boundary layer with a transverse pressure gradient induced by an oblique shock waves

  • 期刊论文

  • 发表日期：

    2025年5月1日

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  • A. A. Sidorenko,
  • S. V. Kirilovskiy,
  • T. V. Poplavskaya

摘要

Results of numerical simulations of interaction of a supersonic boundary layer on a flat plate with an oblique shock wave generated by a thin wedge aligned at a right angle to the plate surface are reported. The problem is solved by means of combining a CFD code based on solving the Reynolds-averaged Navier–Stokes equations with the LOTRAN 3.0 software package based on the eN-method. Specific features of the flow structure with primary and secondary separation regions are identified. It is shown that the shock-induced pressure gradient leads to the development of Tollmien-Schlichting instability waves and crossflow vortex instability.