Abstract:

 A parallel CFD solver for hypersonic flow is developed using the message passing method. 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 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.

Key words: hypersonic;numerical simulation;parallel computation;structured grid