摘要
湍流模型在对复杂流场的数值计算中起着非常重要的作用。本文采用SA一方程湍流模型和SSTk-ω二方程湍流模型,通过解耦求解雷诺平均N-S方程和湍流模型方程实现对亚跨超声速湍流流场的数值模拟。对NACA0012翼型和ONERA-M6机翼跨声速绕流流场进行了计算,对压力分布和激波位置与实验结果进行了细致的比较,并分析了不同离散格式、不同网格疏密及壁面函数对计算结果的影响,在计算过程中这两个模型体现出了较好的简捷性和健壮性。
Turbulence model is very important in the computation of complex flowfield. Two turbulence models applied in this thesis are SA one-equation turbulence model and SST k-ω two-equation turbulence model. In order to complete the numerical simulation of the turbulence flow fields, un-coupled method is used to solve the Reynolds averaged N-S equations and the governing equations for the turbulence models. NACA0012 airfoil flow field and ONERA-M6 wing flow field have been computed, and the accuracy of the shock wave location and Cp distribution is carefully compared with the experimental result. After this, it is shown that the influence to the computational result on different discretize schemes, grid densities and wall function. It is shown that the computation of the two turbulence model carried out are quite simple and robust.
出处
《空气动力学学报》
EI
CSCD
北大核心
2008年第1期85-90,共6页
Acta Aerodynamica Sinica
