摘要
采用格子Boltzmann方法(LBM)的二维9速度(D2Q9)模型和贴体网格,通过引入非均匀网格插值方法和非平衡态外推边界处理,分别结合Baldwin-Lomax(B-L)湍流模型和Spalart-Allmaras(S-A)湍流模型,对高雷诺数Re≥5×105下的NACA0012翼型绕流进行了数值模拟和对比研究,两者的结果与CFL3D的结果和实验结果均吻合的很好,相比之下,采用S-A模型能更好地预测失速迎角,其处理分离流动的能力要强于B-L模型。改进后的LBM适用于非均匀贴体网格,曲边边界,计算简单,并可应用于更复杂的高雷诺数流动中。
Simulation of a high Reynolds number flow （Re≥5×105） around an airfoil （NACA0012） using the Lattice Boltzmann method （LBM） is performed in this article. The present method chooses a two-dimensional 9-velocity （D2Q9） model and uses a non-uniform body-fitted mesh. Originally,the LBM is an incompressible flow solver in orthogonal coordinates. In order to resolve the boundary layer of the airfoil accurately,the algorithm is extended to generalized coordinates. Meanwhile,a non-equilibrium extrapolation scheme for the wall boundary condition is adopted. In order to calculate high Reynolds number flows,the present method is combined with the Baldwin-Lomax （B-L） turbulence model and the Spalart-Allmaras （S-A） turbulence model respectively. The results agrees well with the CFL3D solver results and experimental data. Compared with the B-L model,the S-A model can give more accurate prediction of the static stall angle and show better ability of separated flow simulation. The present method is suitable for problems of non-uniform body-fitted mesh and curvilinear boundary,and its calculation is simple. It can be applied to more complex high Reynolds number flows.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2010年第2期238-243,共6页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金(20061453020)
西北工业大学基础科学研究基金
