改进型k-ε湍流模型在三维侧喷流数值仿真中的应用  

Application of an Improved k- ε Turbulence Model for Numerical Simulation of 3-D Lateral Jet

作　　者：谢春艳[1] 张敬秋 王洋[1] 

机构地区：[1]中国人民解放军63706部队

出　　处：《导弹与航天运载技术》2014年第1期56-60,共5页Missiles and Space Vehicles

摘　　要：采用时间步进法求解三维非稳态雷诺平均N-S方程,得出了标准k??湍流模型及改进型k??湍流模型两种情况下高超声速来流中平板上的圆孔侧喷流流场的稳态解,比较分析了这两种情况下流场对称面的湍动能和湍流粘性比、平板的静压分布、与自由来流垂直的截面上的动压分布。结果表明,改进型湍流模型能抑制激波及滞止点附近的湍动能,使得流场的湍流粘性比更加合理;改进型湍流模型还准确地模拟了喷口前的流动再附点及分离激波,且所得的尾迹区高度及范围与实验结果非常吻合。Three dimension unsteady reynolds-averaged N-S equations was solved using time-marching method, the steady result of circle orifice lateral jet＇ flow field on the flat panel in hypersonic flow was obtained on the condition of the improved k-ε turbulence model and the standard k-ε turbulence model, meanwhile the turbulence kinetic energy and turbulence viscous ratio at the symmetry surface of flow field , the static pressure distributing at flat panel and the dynamic pressure distributing at the section plane perpendicular to free stream on these two conditions were compared and analyzed. The result showed that the improved model could restrain turbulence kinetic energy near the shock wave and stagnation point, which made turbulence viscous ratio of the flow field much more reasonable; it also exactly simulated the flow reattach point and the separation shock wave at front of the orifice, and the height and area of the wake region acquired from this model were very consistent with the experiment result.

关 键 词：高超声速 湍流模型 侧喷流 湍动能 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]