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Abstract <p>The turbulent boundary layer in supersonic flow with an adverse pressure gradient is numerically simulated using the three-parameter differential RANS turbulence model. The adverse pressure gradient is implemented by reducing the Mach number along the plate. The simulation is carried out for a number of values of the free-stream Mach number from 1.5 to 3.0 and the temperature factor equal to and different from unity. The results of calculating the integral and local flow characteristics testify that there is a significant effect of the adverse pressure gradient on the flow and heat transfer characteristics.</p>

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Numerical Study of the Turbulent Boundary Layer with an Adverse Pressure Gradient in Compressible Gas Flow

  • 期刊论文

  • 发表日期：

    2025年2月1日

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  • V. G. Lushchik,
  • S. S. Popovich

摘要

Abstract

The turbulent boundary layer in supersonic flow with an adverse pressure gradient is numerically simulated using the three-parameter differential RANS turbulence model. The adverse pressure gradient is implemented by reducing the Mach number along the plate. The simulation is carried out for a number of values of the free-stream Mach number from 1.5 to 3.0 and the temperature factor equal to and different from unity. The results of calculating the integral and local flow characteristics testify that there is a significant effect of the adverse pressure gradient on the flow and heat transfer characteristics.