Evaluation of engineering turbulence models for complex supersonic flows
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摘要: 对8°,16°,20°,24°超声速二维压缩拐角进行了数值模拟,系统评估了SA(Spalart-Allmaras), k-ω, SST(Shear Stress Transport)3种工程常用湍流模型对激波/边界层干扰复杂流动的模拟适用能力.对于"弱"干扰、小分离,工程常用湍流模型能够较准确地预测其压力、摩擦力、热流分布,而对于"强"干扰、大分离则会造成较大的偏差.同时,随着分离区的增大,各湍流模型的适用性能差别更加明显,数值方法也有一定的影响.Abstract: Supersonic flows past a series of two-dimensional compression ramps were simulated by employing three popular engineering turbulence models, namely Spalart-Allmaras(SA), k-ω, shear stress transport(SST). The performance of the three engineering turbulence models was evaluated and summarized. All three turbulence models are reasonably accurate to predict the surface pressure, skin friction and heat transfer distribution for "weak" shock/boundary-layer interactions, but show significant discrepancies with experimental data for "strong" interactions. Each turbulence model shows much different simulation capability with the separation lengths increased, and the numerical method has much effect too.
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Key words:
- supersonic flow /
- turbulence models /
- shock /
- boundary layers /
- computational fluid dynamics
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[1] Settles G S,Fitzpatrick T J,Bogdonoff S M.Detailed study of attached and separated compression corner flowfields in high Reynolds number supersonic flow[J].AIAA Journal,1979,17(6):579-585 [2] Settles G S,Bogdonoff S M,Vas I E.Incipient separation of a supersonic turbulent boundary layer at high Reynolds number[J].AIAA Journal,1976,14(1):50-56 [3] Settles G S,Vas I E,Bogdonoff S M.Details of a shock-separated turbulent boundary layer at a compression corner[J].AIAA Journal,1976,14(12):1709-1715 [4] Settles G S,Dodson L J.Hypersonic shock/boundary-layer interaction database[R].NASA-CR-177577,1991 [5] Martin M P,Smits A,Wu Minwei,et al.The turbulence structure of shockwave and boundary layer interaction in a compression corner[R].AIAA-2006-497,2006 [6] 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) [7] Yang Xiaodong,Ma Huiyang.Investigation of nonlinear turbulence models for separated supersonic flows[J].Acta Aerodynamica Sinica,2002,20(4):458-463 [8] Wilcox D C.Turbulence modeling for CFD[M].La Canada:DCW Industries,1994:203-205 [9] Spalart P R,Allmaras S R.A one-equation turbulence model for aerodynamic flows[R].AIAA-92-0439,1992 [10] Wilcox D C.Reassessment of the scale determining equation for advanced turbulence models[J].AIAA Journal,1988,26(11):1299-1310 [11] Meter F.Zonal two equation k-ω turbulence models for aerodynamic flows[R].AIAA-93-2906,1993 [12] Gao H,Fu D X,Ma Y W,et al.Direct numerical simulation of supersonic turbulent boundary layer flow[J].Chinese Physics Letters,2005,22(7):1709-1712 -
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