高超声速二方程湍流模型的数值模拟对比

刘景源; 李椿萱

高超声速二方程湍流模型的数值模拟对比

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

作者简介:
刘景源(1976－),男,吉林松原人,博士生,jjliouu@163.com.

中图分类号: V 211.3
计量
- 文章访问数: 2842
- HTML全文浏览量: 44
- PDF下载量: 1136
- 被引次数: 0
出版历程
- 收稿日期: 2006-10-24
- 网络出版日期: 2007-10-31

Comparison of two-equation turbulent models for hypersonic flow simulations

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 对基于Reynolds和Favré(密度加权)混合平均的二方程湍流模型进行了修正,同时根据数值模拟高超声速流动时必须具有高分辨率捕捉间断面与在边界层内抑制数值粘性的能力的要求,提出了新的总变差减小(TVD)格式熵修正函数.在此基础上,通过对压缩拐角的高超声速湍流的数值模拟,对基于Reynolds和Favré混合平均的二方程湍流模型,以及其它不可压缩模型及可压缩性修正模型进行了对比,显示了不同湍流模型及可压缩性修正在计算壁面压力分布和热流分布上的特点,说明了对高超声速压缩拐角型流动,湍流模型可压缩修正的必要性,得到了基于Reynolds和Favré混合平均的二方程湍流模型的计算结果最接近实验结果.
- 湍流模型 /
- 数值模拟 /
- 高超声速 /
- 可压缩性 /
- 热流
Abstract: A two-equation turbulent model based on the mixed Reynolds and Favré (density weighted) average was modified for hypersonic compressible turbulence. In order to suppress the influences of the numerical viscosity toward the boundary layer, and yet to maintain simultaneously the high resolution on capturing the disco ntinuities in the hypersonic flow field, a new entropy correction function was proposed for the total variation diminishing (TVD) scheme. A test case on hypersonic flows over a ramp was then computed using the modified mixed averaged model, as well as the incompressible models proposed by the others together with their respective compressibility correction models. The comparative study shows that the compressibility corrections to the two-equation turbulence models are necessary for hypersonic ramp-type flows, and the numerical results by the modified mixed averaged model are closest to the experiments simultaneously.
- turbulent mode /
- numerical simulation /
- hypersonic /
- compressibility /
- heat transfer

HTML全文

参考文献(1)

[1] Panaras A G. Review of the physics of swept-shock/boundary layer interactions[J]. Prog Aero Sci, 1996, 32:173-244 [2] Knight D, Yan H, Panarasb A G, et al. Advances in CFD prediction of shock wave turbulent boundary layer interactions[J]. Prog Aero Sci, 2003, 39:121-184 [3] Ristorcelli J R, Morrison J H. The Favr-Reynolds average distinction and a consistent gradient transport expression for the dissipation. ICASE-96-19, 1996 [4] Bertin J J, Cummings R M. Fifty years of hypersonics: where we've been, where we're going [J]. Prog Aero Sci, 2003, 39: 511-536 [5] Shyy W, Krishnamurty V S. Compressibility effects in modeling complex turbulent flows[J]. Prog Aero Sci, 1997, 33: 587-645 [6] Liu J Y, Lee C H. A two-equation model for high speed compressible turbulence Lee C H. East-West High Speed Flow Field Conference. Beijing: , 2005:422-437 [7] Grasso F, Falconi D. High-speed turbulence modeling of shock-wave/boundary-layer interaction[J]. AIAA J, 1993, 31(7): 1199-1206 [8] Chien K Y. Prediction of channel and boundary layer flows with a low Reynolds number turbulence model[J]. AlAA J, 1982, 20(1): 33-38 [9] Sinha K, Candler G V. Turbulent dissipation-rate equation for compressible flows[J]. AIAA J, 2003, 41(6): 1017-1021 [10] Chassaing P. The modeling of variable density turbulent flows - A review of first-order closure schemes[J]. Flow, Turbulence and Combustion, 2001, 66: 293-332 [11] Yee H C, Klopfer G H, Montagne J L. High-resolution shock-capturing schemes for inviscid and viscous hypersonic flows[J]. J Comp Phys, 1990, 88: 31-61 [12] Zheng B, Lee C H. The effects of limiters on high resolution computations of hypersonic flows over bodies with complex shapes[J]. Comm Nonlin Sci Numer Simul, 1998, 3(2): 82-87 [13] Lee C H, Zheng B, Wu S P. Numerical computation of hypersonic flows over complex configuration. AIAA-99-3687, 1999 [14] 周伟江, 姜贵庆. 迎风TVD格式在粘性流计算中的应用研究与改进[J]. 计算物理, 1999, 16(4): 401-408 Zhou Weijiang, Jiang Guiqing. The study and modification of upwind TVD scheme for computing viscous flows[J]. Chinese J Comp Phys, 1999, 16(4): 401-408 (in Chinese) [15] Settles G S, Dodson L J. Hypersonic shock/boundary-layer interaction database. NASA-CR-177577, 1991

施引文献

资源附件(0)

访问统计