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将通过物理平面的结构化C型贴体网格变换到计算平面的均匀正交网格,引入非均匀网格插值方法,采用基于Lattice-Boltzm ann方程的D2Q9模型,对低雷诺数下的NACA0012翼型绕流进行了数值模拟,对五个不同位置的边界层速度型与基于有限体积法的CFL3D程序的结果进行了比较。结果表明,两种方法的计算结果一致。改进后的Lattice-Boltzm ann方法适用于曲边边界,非均匀网格,同时对计算速度影响不大。Lattice-Boltzm ann方法计算较简单,因而用LB方法来模拟翼型绕流是一种新的选择,并可应用于更复杂的低雷诺数流动中。
In this paper, we transform the structured C-shaped body-fitted grid to a uniform orthogonal grid in the computational plane by introducing the non-uniform grid interpolation method. The D2Q9 model based on the Lattice-Boltzmann equation is used to simulate the NACA0012 Airfoil flow around the numerical simulation, the boundary layer velocity at five different locations and finite volume method CFL3D program results were compared. The results show that the two methods have the same result. The modified Lattice-Boltzmann method is suitable for curved boundary and non-uniform grid, and has little effect on the calculation speed. The Lattice-Boltzmann annotation method is relatively simple to calculate. Therefore, the LB method is a new choice to simulate the airfoil flow and can be applied to the more complex low Reynolds number flow.