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本文采用MPI消息传递模式自主开发出适用于高超声速流动数值模拟的并行计算软件,该软件以三维Navier-Stokes方程为基本控制方程来求解层流问题,应用基于结构网格的有限体积法对计算域进行离散,采用AUSMPW+格式求解对流通量,利用MUSCL插值方法获得高阶精度,时间格式上采用LU-SGS方法进行时间迭代以加快求解定常流动的收敛过程。在高性能计算机上针对不同高超声速流动进行大规模并行计算的结果表明,所开发的CFD并行计算软件具有较高的并行计算效率,为高超声速飞行器气动力/热的准确预测提供了高效工具。
In this paper, MPI messaging model independently developed for the supersonic flow numerical simulation of parallel computing software, the software to three-dimensional Navier-Stokes equation as the basic control equations to solve the laminar flow problem, the application of finite volume method based on the structure of the grid calculation Domain is discretized. AUSMPW + format is used to solve the convection flux and the MUSCL interpolation method is used to obtain high-order accuracy. The LU-SGS method is used for time iteration in time format to speed up the convergence of the steady flow. The results of large-scale parallel computation on high-performance computers for different hypersonic flows show that the developed CFD parallel computing software has higher parallel computing efficiency and provides an efficient tool for accurate aerodynamic / thermal prediction of hypersonic vehicles.