Scholarlink

Abstract <p>Numerical study of a compressible turbulent boundary layer in supersonic flow with adverse and favorable pressure gradients is carried out using the three-parameter differential RANS turbulence model. The pressure gradients are implemented by changing the Mach number of the free-stream flow along the plate. The study is carried out for a number of the free-stream Mach numbers (from 1 to 3) and two values of the temperature factor (0.5 and 1.5). Using the results of calculations of the flow and heat transfer characteristics, the dependences of the Reynolds analogy coefficient on two pressure gradient parameters are obtained.</p>

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Reynolds Analogy Coefficient in a Compressible Turbulent Boundary Layer with a Pressure Gradient

  • 期刊论文

  • 发表日期：

    2025年12月1日

查看全文
  • V. G. Lushchik,
  • A. I. Reshmin

摘要

Abstract

Numerical study of a compressible turbulent boundary layer in supersonic flow with adverse and favorable pressure gradients is carried out using the three-parameter differential RANS turbulence model. The pressure gradients are implemented by changing the Mach number of the free-stream flow along the plate. The study is carried out for a number of the free-stream Mach numbers (from 1 to 3) and two values of the temperature factor (0.5 and 1.5). Using the results of calculations of the flow and heat transfer characteristics, the dependences of the Reynolds analogy coefficient on two pressure gradient parameters are obtained.