NACA4412翼型低速绕流数值计算中湍流模型对比

使用Spalart-Allmaras(S-A)、SSTk-ω、Gao-Yong 3种湍流模型对NACA4412翼型低速绕流进行了数值计算,研究了尾迹流动松弛效应。对流项采用Roe格式离散,扩散项采用二阶中心格式离散,离散后的控制方程用多步Runge-Kutta显示时间推进法求解。计算中对翼型尾缘流松弛效应进行了分析,比较了翼型表面压力系数、速度剖面、雷诺应力等的分布,3种湍流模型总体上能够较好地模拟NACA4412翼型低速绕流。SSTk-ω模型对流动细节及升力系数计算最好,Gao-Yong模型对翼型平均速度剖面及雷诺剪切应力分布计算最准确。

Comparison of turbulence models for numerical simulation of low-speed flow around NACA4412 airfoil

Numerical simulation of the flow around the NACA4412 airfoil is implemented based on Spalart-Allmaras (S-A), SST k-ω and Gao-Yong turbulence models.In our procedures,convection terms and diffusion terms are calculated using Roe scheme and center difference scheme respectively.The Runge-Kutta time marching method is employed to solve space dis-crete control equations.The flow relaxation effect at the NACA4412 airfoil trailing edge is analyzed with the models.The pressure distribution on the wall surface,velocity profile distribution and Reynolds stress distribution obtained with the three models are compared.The numerical results obtained using the three turbulence models agree with the experimental data well in general.SST k-ω turbulence model gets the best flow details and lift coefficient.The Gao-Yong turbulence model can simulate most accurately for mean velocity profiles and Reynolds shear stress.