摘要
采用GAO-YONG可压缩湍流方程组,模拟了平板激波/湍流边界层干扰现象.运用SIMPLE算法求解方程组,并分别采用三阶精度的QUICK格式和中心格式离散对流项和扩散项.计算结果较好预测了入射斜激波在平直壁面引起湍流附面层分离的流动特征:分离点的反射激波、分离包引起的膨胀扇以及再附点的反射激波.对流场的时均参数与实验值进行了比较,计算得到的壁面压力分布、摩阻系数分布和速度型与实验值比较吻合很好.结果表明GAO-YONG可压缩湍流方程组能够高精度模拟平板激波/湍流边界层干扰流动.
Rational GAO-YONG compressible turbulence equations were applied to simulate numerically the flat plate shock wave/turbulent boundary layer interactions. The equations were solved using the semi-implicit method for pressure-linked equations （SIMPLE） algorithm. The discretization of convection and diffusion terms were respectively adopted quadratic upwind interpolation of convective kinematics（QUICK） scheme with third-order precision and center difference （CD） scheme. The calculational results predict well the flow characteristics of turbulent boundary layer separation induced by incident shock wave ： a separation shock followed by expansion fan around separation bubble and shock in reattachment point. The computational results of the time-averaged parameters, such as the velocity profiles along the x-coordinate, pressure along the wall surface and skin-friction coefficient along the wall were compared with the experimental results. It is shown that when the GAO-YONG compressible turbulence equations are applied to the shock wave/turbulent boundary layer interacting cases, the basic feature and details of shock flows can be well simulated.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2007年第10期1136-1140,共5页
Journal of Beijing University of Aeronautics and Astronautics
关键词
可压缩流
湍流
激波
边界层
compressible flow
turbulence
shock waves
boundary layer
