低雷诺数下翼型绕流的格子Boltzmann方法数值模拟

The numerical simulation of flow around airfoil at low Reynolds number by using lattice Boltzmann method

文章采用混合格子Boltzmann方法模拟NACA0012翼型流场分离,该方法是将标准格子Boltzmann方法与非结构化有限体积方程相结合的一种方法。首先,分析不同网格分辨率下的计算精度;然后,分析了在雷诺数等于103的情况下不同攻角下翼型的气动特性;最后,计算了不同雷诺数下攻角为0°时的翼型流场。结果证明,混合格子Boltzmann方法在固体壁面有较高的计算精度,可以准确地评估翼型绕流流场。

In this paper, hybridlattice Boltzmann method is used to simulate NACA0012 airfoil flow field separation. Hybrid lattice Boltzmann method combines standard lattice Boltzmann method with unstructured finite volume formulation. This paper first analyzes the calculation accuracy under different grid resolutions, and then analyzes the aerodynamic characteristics of the airfoil under different angles of attack when the Reynolds number is equal to 103. Finally, the airfoil flow field with different angle of attack at 0 ° with different Reynolds numbers was calculated. The results show that the hybridlattice Boltzmann method has a high calculation accuracy at wall boundary and can accurately evaluate the flow field around the airfoil.