激波-边界层-分离流相互干扰三维湍流的数值模拟  

NUMERICAL SIMULATION OF THREE DIMENSIONAL SHOCK WAVE-BOUNDARY LAYER-SEPERATED FLOW INTERACTIONS

作　　者：韩振学[1] 方韧[1] 纪永春 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1998年第2期144-148,共5页Journal of Aerospace Power

摘　　要：本文采用数值方法求解时间相关三维可压缩雷诺平均Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程组，模拟激波—边界层—分离流相互干扰三维湍流流动。湍流模型为Ｂａｄｗｉｎ－Ｌｏｍａｘ两层代数模型，改进后用于三维内流问题。采用单元中心有限体积法离散流场控制方程，ＶａｎＬｅｅｒ矢通量格式计算无粘通量，中心差分法计算粘性通量，ＬＵＳＧＳ时间推进格式计算定常流场。本文以二元跨音速扩压器内三流动为算例，数值模拟较强激波—边界层—分离流相互干扰维湍流流动，并与实验结果进行了比较。数值模拟结果，在激波强度、分离点位置和再附点位置等方面，与实验结果吻合较好。Three dimensional turbulent flows with strong shock wave-boundary layer-seperated flow interactions are numerically simulated.Time-dependent compressible Navier-Stokes equations in conjunction with Baldwin-Lomax turbulence model are discrete with finite volume method and LUSGS time marching scheme to get the steady flowfields.Inviscid flux and viscous flux on the control volume surfaces are calculated with Van Leer flux vector splitting scheme and central difference scheme separatelly.The numerical methods are valid for 3D transonic flow through a diffuser.The computational results are in a good agreement well with the experimental data of Mach number before the shock wave,separation and reattachment positions.

关 键 词：激波 边界层 分离流 相互作用 数值模拟 湍流 

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]