扩压器内跨音速湍流的数值模拟  

NUMERICAL PREDICTION OF TWO-DIMENSIONAL TRANSONIC TURBULENT FLOW IN A DIFFUSER

作　　者：韩振学[1] 方韧[1] 钟子兵 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1997年第3期279-282,共4页Journal of Aerospace Power

基　　金：国防科技预研基金

摘　　要：采用Ｊｏｈｎｓｏｎ－Ｋｉｎｇ非平衡代数雷诺应力湍流模型（Ｊ－Ｋ模型）和Ｂａｌｄｗｉｎ－Ｌｏｍａｘ零方程湍流模型（Ｂ－Ｌ模型），数值模拟较强激波／边界层相互作用时扩压器内的分离流动。计算结果与实验值进行了比较，表明Ｊ－Ｋ模型比Ｂ－Ｌ代数湍流模型可较好地计算出分离流动的再附点位置，并且可更好地计算出激波强度和沿流程的压力分布，仅增加很少的计算量，并更易推广应用于三维湍流问题的数值模拟。Two-dimensional transonic flow in a diffuser is numerically invesgated by solving 2D time-dependent Reynolds-averaged compressible Navier-Stockes equations.The numerical method is based on Van-Leer's flux splitting cell-centered finite volume scheme.Baldwin-Lomax algebraic turbulence model and Johnson-King non-equilibrium turbulence model are tested to simulate largely separated flow.Comparison of the computational results with corresponding experimental data shows that the predicted wall static pressure distributions and shock strength by both two turbulence models agree well with the experimental data,but Johnson-King model does better than Baldwin-Lomax model in the prediction of separation reattachment point.

关 键 词：激波 边界层 干扰 数值计算 湍流 扩压器 跨音速 

分 类 号：O357.5[理学—流体力学] V211.19[理学—力学]