雷诺应力模型的初步应用

针对SSG/LRR-ω雷诺应力模型,选取NASA湍流资源网站上的四个典型算例,即湍流平板边界层流动、带凸起管道流动、翼型尾迹区流动和NACA0012不同攻角绕流,开展初步的验证与确认工作,将部分结果和CFL3D进行对比。对于NACA0012翼型绕流,对比雷诺应力模型和SA模型的升力系数,结果表明:在失速攻角附近,雷诺应力模型明显优于SA模型。在此基础上,将该模型应用于DLR-F6翼身组合体的数值模拟,计算得到的机翼表面典型站位压力分布和实验值吻合良好,同时该模型捕捉到翼身交汇位置的小范围分离。

Preliminary application of Reynolds stress model

Focusing on the verification and validation of SSG/LRR-w reynolds stress model, four typical two dimensional cases from NASA turbulence resources website are chosen, including zero pressure gradient flat plate, bump-in-channel, airfoil near-wake and NACA0012 airfoil. Numerical results are in good agreement with that of CFL3D and experiment. For flow over NACA0012 airfoil, lift coefficients of reynolds stress model and SA model are compared. It is obvious that near the stall angle of attack, reynolds stress model has advantages over SA model. Based on these results, SSG/LRR- reynolds stress model is applied to the simulation of complex DLR-F6 wing-body configuration. Pressure coefficient in typical stations is comparable to that of experiment. Besides, small range of separation in the wing-body intersection is well captured.