高超声速流动湍流模式评估  

Turbulence modeling validation in hypersonic flows

作　　者：耿云飞[1] 阎超[1] 徐晶磊[1] 康宏琳[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《北京航空航天大学学报》2011年第8期907-911,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金资助项目(90716010)

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。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.

关 键 词：高超声速 湍流模式 可压缩修正 计算流体力学 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]