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

作　　者：聂胜阳[1] 高正红[1] 黄江涛[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力国防科技重点实验室,陕西西安710072

出　　处：《空气动力学学报》2012年第1期52-56,共5页Acta Aerodynamica Sinica

摘　　要：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.

关 键 词：涡粘性假设 微分雷诺应力模型 压缩性修正 激波位置 流动分离 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]