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Abstract <p>For the compressible turbulent boundary layer, the results of the numerical study using the three-parameter RANS turbulence model are compared with the results of direct numerical simulation (DNS). It is shown that the calculation results using the RANS model are in satisfactory agreement with the DNS results at the Mach numbers from 6 to 14. This makes it possible to recommend the use of the RANS model in engineering calculations of the hypersonic boundary layer when there is no need for powerful computing systems.</p>

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Turbulent Boundary Layer on a Plate in Compressible Gas Flow

  • 期刊论文

  • 发表日期：

    2025年6月17日

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  • V. G. Lushchik,
  • A. I. Reshmin

摘要

Abstract

For the compressible turbulent boundary layer, the results of the numerical study using the three-parameter RANS turbulence model are compared with the results of direct numerical simulation (DNS). It is shown that the calculation results using the RANS model are in satisfactory agreement with the DNS results at the Mach numbers from 6 to 14. This makes it possible to recommend the use of the RANS model in engineering calculations of the hypersonic boundary layer when there is no need for powerful computing systems.