基于自适应笛卡尔网格的翼型绕流数值模拟

Numerical Simulation of Flows around Airfoil Based on Adaptively-refined Cartesian-mesh Approaches

基于自适应笛卡尔网格方法求解Euler方程,结合浸入式边界方法解决小切割网格单元的时间步长限制问题,对NACA0012翼型的两种流动状况进行了数值模拟;并与AGARD的理论解和结构网格解进行了对比。结果表明:自适应笛卡尔网格方法在较少的网格量上得出的计算结果与AGARD结果吻合的很好,能够有效模拟二维翼型绕流问题,表明该网格方法具有进一步扩大应用范围的前景。

Adaptively-refined Cartesian-mesh approaches for the computation of Euler equations were intro- duced, immersed boundary method was employed to relieve the time step restriction of small cut cell, and two flows around NACA0012 airfoil were simulated and compared with theoretical and structured mesh results provided by AGARD. The results achieves from AGARD and flows around 2D airfoil less number of mesh cells show good agreement with the published data by are efficiently simulated, which show prospective applications in much more fields.