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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。
Two supersonic supersonic inflatable ellipsoidal inflows and supersonic inflatable inflatable corners were chosen as the reference flow. Several popular turbulence models, such as BL (Baldwin-Lomax), SA Spalart-Allmaras mode, k-ω mode and SST (Shear-Stress Transport) mode. By comparing and analyzing the numerical and experimental results, the relevant turbulence models are evaluated and some meaningful conclusions are obtained. Influenced by the flow compressibility, the corresponding compressible correction of the existing turbulence model should be made when calculating the hypersonic turbulent wall heat flux.