不同湍流模型在低雷诺数流动中的应用研究  

Research on Turbulent Models at the Low Reynolds Number Flow

作　　者：陈立立[1] 郭正[1] 

机构地区：[1]国防科技大学航天科学与工程学院,长沙410073

出　　处：《现代应用物理》2016年第3期48-52,共5页Modern Applied Physics

摘　　要：以SD7032翼型为研究对象,基于求解雷诺平均N-S方程的有限体积法,采用S-A、k-w、SSTk-w、realizable k-ε、transition SST和改进的γ-Re_(θ,t)转捩模型等6种湍流模型,对雷诺数为203 800时翼型流动进行了数值模拟,评估了不同湍流模型在低雷诺数流动中的升阻特性和收敛情况。结果表明:当不考虑流动转捩时,和其他湍流模型相比,SSTk-w湍流模型计算得到的升阻系数更接近实验值,能够较好地模拟低雷诺数流动。考虑转捩时,改进后的γ-Re_(θ,t)转捩模型的稳定性和收敛性都有较大提升,在小攻角范围内计算结果和实验值吻合。Numerical simulation of the flow over SD7032 airfoil was performed using the RANS method by solving the Navier Stokes （N-S）equations with six turbulence models operating at the low Reynolds number of 203 800. The lift and drag coefficients and conver- gences of six turbulence models at the low Reynolds number flow were evaluated. The results showed that when taking no consideration of flow transition, the lift and drag coefficients calculated by SST κ-ω model could be approximated by the experimental value. However, when taking flow transition into consideration, stability and convergence performances of modified γ-Reθ,ttransition model got significantly improved, the calculation results agreed with the experimental values within a small attack angle.

关 键 词：低雷诺数流动 SD7032翼型 湍流模型 γ-Reθ t转捩模型 

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]