非线性EASM在激波与湍流边界层 相互作用中的数值应用

赵慧勇; 雷波; 乐嘉陵

非线性EASM在激波与湍流边界层相互作用中的数值应用

1.
西南交通大学牵引动力国家重点实验室,成都 610031
2.
中国空气动力研究与发展中心计算空气动力研究所,四川绵阳 621000

基金项目: 国家高技术研究发展计划(2006AA1149)

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出版历程
- 收稿日期: 2010-03-22
- 修回日期: 2010-12-30
- 刊出日期: 2011-04-28

Numerical application of nonlinear EASM model to the interaction between shock waves /turbulent boundary layer

1.
Traction Power State Key Laboratory of Southwest Jiaotong University, Chengdu 610031,China
2.
Computational Aerodynamics Institute, China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China

摘要

摘要: 采用基于k-ω湍流模型的非线性显式代数应力模型(EASM)对超燃冲压发动机常用的超声速凹槽、压缩拐角和侧壁压缩进气道简化模型的激波与湍流边界层的相互作用进行了计算,主要研究了EASM模型对壁面压强、摩阻、Stanton数和壁面摩擦力线的计算精度,计算结果与SST (shear stress transport)模型进行了比较.EASM模型对壁面压强、摩阻和Stanton数的计算精度较高,值得进一步推广应用.在壁面热流和摩擦力线的计算中EASM模型比SST模型的精度更高.
- 进气道 /
- 计算流体动力学 /
- 激波 /
- 边界层 /
- 湍流模型 /
- Stanton数
Abstract: The nonlinear explicit algebraic stress model (EASM) in k-ω form was used to compute the interaction between shock wave and turbulent boundary layer of supersonic cavity,compression corner and simplified model of side-compression inlet which are usually used in scramjet engine.The main focus was computational resolution of EASM model on wall pressure,friction,Stanton number and skin friction lines.The computational results of EASM model were compared with those of SST (shear stress transport) model.EASM model has better computational resolution on wall pressure,friction and Stanton number so that it can be generalized.EASM model is better than SST model in computation of Stanton number and skin friction lines.
- inlets /
- computational fluid dynamics /
- shock waves /
- boundary layer /

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参考文献(12)

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