运用GAO-YONG湍流模型对扩压器内跨声速流动的数值模拟  

Numerical simulation of transonic flows in a diffuser with GAO-YONG turbulence equations

作　　者：伏晓艳[1] 高歌[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《推进技术》2008年第2期139-142,共4页Journal of Propulsion Technology

摘　　要：运用GAO-YONG可压缩湍流方程组,采用同位网格SIMPLE算法,对扩压器跨声速流动中的二维激波/湍流边界层干扰现象进行了数值模拟。将计算得到的流场的时均参数与实验值进行比较,数值模拟结果在激波强度、壁面压力分布以及分离点和再附点位置等方面,与实验值吻合较好,表明GAO-YONG可压缩湍流方程组能够比较准确的模拟较强激波/湍流边界层干扰流动,从而进一步为GAO-YONG湍流模型的正确性及其在可压缩流场模拟方面的适用性提供了佐证。The two-dimensional shock wave/turbulent boundary layer interactions in a diffuser is numerically investigated by solving GAO-YONG compressible turbulence equations and using SIMPLE algorithm on non-staggered grids. Comparison of the computational results of the time-averaged parameters with corresponding experimental data shows that the shock strength, pressure along the wall surface, separation point and reattachment point agree well with the experimental data. The computational results indicate that the GAO-YONG compressible turbulence equations can well and truly simulate shock wave/ turbulent boundary layer interactions in transonic flows. This numerical simulation can further prove the correctness and the applicability of the GAO-YONG compressible turbulence model.

关 键 词：湍流 数值计算 激波/湍流边界层干扰 GAO-YONG 可压缩湍流方程 

分 类 号：V231.21[航空宇航科学与技术—航空宇航推进理论与工程]