学术
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.[著者文摘]
文章出处:
《北京航空航天大学学报》-2007年33卷10期 -1136-1140页
栏目信息:
文献标识码:
A
文章编号:
1001-5965（2007）10-1136-05
Computation of shock wave/boundary-layer interactions with GAO-YONG turbulence equations
Xu Libo ,Gao Ge （ National key Laboratory on Aero-Engines, Beijing University of Aeronautics, and Astronautics Beijing 100083, China）
Abstract:
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.[著者文摘]
Key words:
compressible flow ; turbulence ; shock waves ; boundary layer
更多>>免费文章
cqvip.com