Large Eddy Simulations for Transitional and Turbulent Flows in Mixing Layers

机译：混合层中过渡流动和湍流的大涡模拟

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In this paper, two types of 3-D spatial evolving compressible mixing layers, namely, supersonic/supersonic mixing layers and supersonic/subsonic mixing layers, are studied. The transition process and fully developed turbulent flows in different convective Mach numbers are investigated using the large eddy simulation (LES) method. The computational results show that the most instable disturbance mechanism is the 3-D oblique wave perturbation in high convective Mach number. A vortices dominate the transition process. The consistency of LES results to natural transition and the relevant literature data indicates that is reasonable to investigate mixing layer development by induce linear disturbance. Shocklets which distribute unsymmetrical have been captured by the LES method at the convective Mach number 1.0. Their shapes are similar to experiment results. In the fully developed turbulence region, velocity pulse tendency towards isotropy and the compressibility effect increases with the convective Mach number.

机译：本文研究了两种类型的3-D空间演化可压缩混合层，即超音速/超音速混合层和超音速/亚音速混合层。使用大涡模拟（LES）方法研究了不同对流马赫数下的过渡过程和充分发展的湍流。计算结果表明，在高对流马赫数下，最不稳定的扰动机制是3-D斜波扰动。涡旋主导着过渡过程。 LES结果与自然转变的一致性，相关文献数据表明通过诱导线性扰动研究混合层发育是合理的。通过对流马赫数为1.0的LES方法已捕获了分布不对称的小波。它们的形状与实验结果相似。在充分发展的湍流区域，速度脉冲趋于各向同性的趋势和可压缩性效应随对流马赫数的增加而增加。

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来源
《Proceedings of the 3rd Sino-Italian conference on space aerothermodynamics and hot structures》|2011年|135-144|共10页
会议地点 Shanghai(CN)
作者
PAN Hong-lu; MA Han-dong; WANG Qiang;
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作者单位

China Academy of Aerospace Aerodynamics, Beijing 100074, China;

China Academy of Aerospace Aerodynamics, Beijing 100074, China;

China Academy of Aerospace Aerodynamics, Beijing 100074, China;

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会议组织
原文格式 PDF
正文语种 eng
中图分类航天器空气动力学;
关键词
compressible mixing layer; transition; turbulence; large eddy simulation; direct numerical simulation;

机译：可压缩混合层;过渡;湍流;大涡模拟;直接数值模拟;

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Large Eddy Simulations for Transitional and Turbulent Flows in Mixing Layers

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