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首页> 外文期刊>Journal of Spacecraft and Rockets >Compressibility Considerations for k-ω Turbulence Models in Hypersonic Boundary-Layer Applications
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Compressibility Considerations for k-ω Turbulence Models in Hypersonic Boundary-Layer Applications

机译：高超声速边界层应用中k-ω湍流模型的可压缩性考虑

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摘要

The ability of κ-ω models to predict compressible turbulent skin friction in hypersonic boundary layers is investigated. Although uncorrected two-equation models can agree well with correlations for hot-wall cases, they tend to perform progressively worse (particularly for cold walls) as the Mach number is increased in the hypersonic regime. Simple algebraic models such as Baldwin-Lomax perform better compared to experiments and correlations in these circumstances. Many of the compressibility corrections described in the literature are summarized here. These include corrections that have only a small influence for κ-ω models or that apply only in specific circumstances. The most widely used general corrections were designed for use with jet or mixing-layer free-shear flows. A less-well-known dilatation-dissipation correction intended for boundary-layer flows is also tested and is shown to agree reasonably well with the Baldwin-Lomax model at cold-wall conditions. It exhibits a less dramatic influence than the free-shear type of correction. There is clearly a need for improved understanding and better overall physical modeling for turbulence models applied to hypersonic boundary-layer flows.
机译：研究了κ-ω模型预测高超声速边界层中可压缩湍流皮肤摩擦的能力。尽管未经校正的两方程模型与热壁情况的相关性非常吻合，但随着高超声速马赫数的增加，它们往往表现得越来越差（特别是对于冷壁）。在这些情况下，与实验和相关性相比，像Baldwin-Lomax这样的简单代数模型的性能更好。这里总结了文献中描述的许多可压缩性校正。其中包括对κ-ω模型影响很小或仅在特定情况下适用的校正。设计最广泛使用的常规修正值是用于射流或混合层自由剪切流量。还测试了一个不太为人所知的用于边界层流动的膨胀-耗散校正，并显示出与冷壁条件下的Baldwin-Lomax模型相当吻合。与自由剪切类型的校正相比，它显示的影响较小。显然，需要对应用于高超声速边界层流的湍流模型进行更好的理解和更好的整体物理建模。

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