Turbulent Boundary Layer on a Plate in Compressible Gas Flow

IF 0.6 4区工程技术 Q4 MECHANICS

Fluid Dynamics Pub Date : 2025-06-17 DOI:10.1134/S0015462825600439

V. G. Lushchik, A. I. Reshmin

引用次数: 0

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.

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可压缩气体流动中平板湍流边界层

对于可压缩湍流边界层，将三参数RANS湍流模型的数值研究结果与直接数值模拟（DNS）的结果进行了比较。结果表明，在马赫数6 ~ 14范围内，采用RANS模型的计算结果与DNS计算结果吻合较好。这使得在不需要强大的计算系统的情况下，推荐在高超声速边界层的工程计算中使用RANS模型成为可能。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Fluid Dynamics MECHANICS-PHYSICS, FLUIDS & PLASMAS

CiteScore

1.30

自引率

22.20%

发文量

审稿时长

6-12 weeks

期刊介绍： Fluid Dynamics is an international peer reviewed journal that publishes theoretical, computational, and experimental research on aeromechanics, hydrodynamics, plasma dynamics, underground hydrodynamics, and biomechanics of continuous media. Special attention is given to new trends developing at the leading edge of science, such as theory and application of multi-phase flows, chemically reactive flows, liquid and gas flows in electromagnetic fields, new hydrodynamical methods of increasing oil output, new approaches to the description of turbulent flows, etc.