Abstract
According to the instruction of message passing interface (MPI), A parallel CFD solver for hypersonic flow is programmed. The code employs the 3D Navier-Stokes equations as the basic governing equations to simulate the laminar hypersonic flow. The cell centered finite volume method based on structured grid 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. Ghost cells are applied to treat the boundary conditions, and the physical data at the ghost cells of internal connected boundary are overwritten by the data of adjacent block when each iteration step come to an end. The data communication is carried out by the MPI process. The parallel solver has been run 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 aerodynamic and aerothermodynamic environment for hypersonic flight vehicles.
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