基于LBM-LES方法前缘多孔翼型流场的数值分析

Numerical Analysis of Flow Field for Leading-edge Porosity Airfoil Based on LBM-LES Method

前缘多孔翼型能够有效降低翼型的气动噪音,但是其对流场特性的影响还需进一步的研究。采用基于Lattice Boltzmann Method(LBM)与Large Eddy Simulation(LES)结合的LBM-LES方法对雷诺数为Re=3.5×10~6下的标准GAW-1翼型与前缘多孔GAW-1翼型进行了数值模拟,分析并比较了不同迎角下的流场结构。其中,粒子速度模型采用D2Q9模型,LES采用动态Smagorinsky亚格子模型对湍流进行模拟。数值分析结果表明:LBM-LES方法可以准确地捕捉非定常高雷诺数下湍流流场的流动分离特征,且数值结果可以很好的与实验值吻合;其中,在迎角低于4°的情况下前缘多孔介质对翼型气动特性影响较小,随迎角的增大其对气动特性的影响增大。

The leading edge porosity airfoil can effectively reduce the aerodynamic noise of the airfoil,but its influence on characteristics of the flow field needs further study.The LBM-LES method combines with the Lattice Boltzmann Method(LBM) and Large Eddy Simulation(LES) was used to numerical simulation the standard GAW-1 wing and leading edge porous GAW-1 airfoil at high Reynolds number Re=3.5×10~6,the flow features at different angles of attack was analyzed and compared.Where D2Q9 model is used as particle velocity model and LES uses a dynamic Smagorinsky subgrid model to simulate turbulence.The results shows that LBM-LES method can accurately capture the flow separation characteristics of turbulent flow field under unsteady high Reynolds number and the numerical results can be well consistent with the experimental values.Moreover,the leading edge porous medium has little effect on the aerodynamic characteristics of the airfoil,and the influence on the aerodynamic characteristics increases with the increase of the angle of attack.