基于结构网格的高超声速流动大规模并行数值模拟研究

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。

Massively Parallel Numerical Simulation of Hypersonic Flow Based on Structured Grids

A parallel CFD solver for hypersonic flow is developed using the message passing method. The code employs the 3DNavier-Stokes equations as the basic governing equations to simulate the laminar hypersonic flow.The cell centered finite volume method based on structured grids is applied for spatial discretization.The AUSMPW+scheme is used for the inviscid fluxes,and the MUSCL approach is used for higher order spatial accuracy.The implicit LU-SGS scheme is applied for time integration to accelerate the convergence of computations in steady flows.Massively parallel computations are carried out on high performance computers to simulate different hypersonic flows.The numerical results show that the parallel CFD solver has high computational efficiency,and it can be used for the accurate prediction of the aerodynamic and aerothermodynamic environments for hypersonic flight vehicles.