高超声速流动湍流模式评估

耿云飞; 阎超; 徐晶磊; 康宏琳

高超声速流动湍流模式评估

北京航空航天大学航空科学与工程学院, 北京 100191

基金项目: 国家自然科学基金资助项目(90716010)

详细信息

作者简介:
耿云飞(1984-),男,河北石家庄人,博士生,fifigeng@yahoo.com.cn.

中图分类号: V 211.3
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- 被引次数: 0
出版历程
- 收稿日期: 2010-03-16
- 网络出版日期: 2011-08-30

Turbulence modeling validation in hypersonic flows

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 选取了超声速二维膨胀-压缩拐角和高超声速双椭球绕流作为基准流动,考察了几种当前CFD(Computational Fluid Dynamics)工程应用较流行的湍流模式:BL(Baldwin-Lomax)模式、SA(Spalart-Allmaras)模式、k-ω模式以及SST(Shear-Stress Transport)模式,通过数值计算结果和实验结果的对比及分析,对有关的湍流模式进行了评估,得到一些有意义的结论,并指出受流动可压缩效应的影响,计算高超声速湍流壁面热流时要对现有的湍流模式进行相应的可压缩修正.
- 高超声速 /
- 湍流模式 /
- 可压缩修正 /
- 计算流体力学
Abstract: To provide accurate numerical solutions for selected supersonic/hypersonic flow fields and to compare and evaluate the performance of selected turbulence models with experimental results,four popular turbulence models were tested and validated against experimental data of two turbulent flows. The investigated flows are 2D supersonic expansion-compression corner and hypersonic double ellipsoid. The tested turbulent models were: zero-equation model of Baldwin-Lomax(BL), one-equation model of Spalart-Allmaras(SA), two-equation k-ω/k-ε shear-stress transport(SST) model of Menter and two-equation k-ω model of Wilcox. It shows that the formal turbulent models are competent for the present supersonic flows. However, the simulation of the hypersonic flow, especially for flows at high angle of attack, compressibility modification is needed.
- hypersonic /
- turbulence model /
- compressibility modification /
- computational fluid dynamics

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参考文献(1)

[1] Knight D.RTO WG 10:test cases for CFD validation of hypersonic flight .AIAA 2002-0433,2002 [2] Knight D,Yan H,Panaras A,et al.RTO WG 10:CFD validation for shock wave turbulent boundary layer interactions .AIAA 2002-0437,2002 [3] 张红杰,马晖扬,童秉纲.高超声速复杂流动中湍流模式应用的评估[J].空气动力学学报,2001,19(2):210-216 Zhang Hongjie,Ma Huiyang,Tong Binggang.Turbulence modeling validation in hypersonic complex flows[J].Acta Aerodynamica Sinica,2001,19(2):210-216(in Chinese) [4] 贺旭照.高超声速飞行器气动力气动热数值求解和超声速流动的区域推进求解 .绵阳:中国空气动力与发展中心研究生部,2007 He Xuzhao.Numerically simulate aero-force & heat of hypersonic vehicles and region marching method for supersonic flow simulation .Mianyang:Graduate School,China Aerodynamics Research and Development Center,2007(in Chinese) [5] 康宏琳.高超声速湍流气动加热的数值模拟研究 .北京:北京航空航天大学航空科学与工程学院,2007 Kang Honglin.Numerical simulation of aerodynamic heating in hypersonic turbulent flows .Beijing:School of Aeronauti Science and Engineering,Beijing University of Aeronautics and Astronautics,2007(in Chinese) [6] Baldwin B S,Lomax H.Thin layer approximation and algebraic model for separated turbulent flows .AIAA 78-257,1978 [7] Spalart P R,Allmaras S R.A one-equation turbulence transport model for aerodynamics flows .AIAA 92-0439,1992 [8] Wilcox D C,Traci R M.A complete model of turbulence .AIAA 76-351,1976 [9] Menter F R.Two equation eddy viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605 [10] Johnson D A,King L S.A mathematical simple turbulence closure model for attached and separated turbulent boundary layers[J].AIAA Journal,1985,23(11):1684-1692 [11] Aymer D,Aliziary T,Carlomagno G,et al.Experimental study of the flow around a double ellipsoid configuration //Hypersonic Flows for Reentry Problems.Antibes,France:Springer-Verlag,1991:335-357 [12] Morkovin M V.Effects of compressibility on turbulent flows //The Mechanics of Turbulence.Paris:CNRS,1962:367-380 [13] 韩省思,叶桃红,朱旻明,等.一个新的可压缩性修正的k-ε模型[J].空气动力学学报,2009,27(6):677-682 Han Xingsi,Ye Taohong,Zhu Minming,et al.A new k-ε turbulent model with compressibility modifications[J].Acta Aerodynamica Sinica,2009,27(6):677-682 (in Chinese) [14] Wilcox D C.Turbulence modeling for CFD[M].2nd ed.California:DCW Industries Inc,1998

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