微分雷诺应力模型在激波分离流中的应用

Differential Reynolds stress model for shock & separated flow

由于Boussinesq涡粘性假设的湍流模型在一些流动中如激波分离流中预测失真,本文介绍一种基于完全雷诺应力方程的微分雷诺应力模型(DRSM),应用压缩性修正和改进耗散率方程构造出应用于可压流体的可实现DRSM,SSG压应力模型测试了两组参数。将其应用于ONERA M6机翼在跨声速大攻角的计算,结果表明DRSM能更好地模拟激波位置和流动分离。

While models based on the Boussinesq eddy-viscosity approximation provide different predictions for flows like shock and separated flow which differ greatly from corresponding measurements.A model based on full Reynolds-stress equation called Differential Reynolds Stress Models（DRSM） will be presented in this paper.Compressibility modification and an improved dissipation rate equation are accounted to improve a realizable model for real compressible flow,two groups of Closure Coefficients of SSG pressure strain model were tested.DRSM performs well when applying to the ONERA-M6-Wing at subsonic speeds at high angle of attack,especially the accuracy of the shock location and flow separation.