Numerical Simulation of Supersonic Flow with Shock Wave using Modified AUSM Scheme

摘要

To analyze the hypersonic vehicle, comprehensive numerical has been performed. The numerical simulation is based on a finite-volume approximation. The inviscid flux vectors are discretized by the modified advection upstream splitting method (MAUSM) with shock capturing character. The MAUSM algorithms for introducing artificial dissipation into a central difference approximation to the Navier-Stokes equations are considered. The focus of the paper is on the convective upwind and split Mach No. scheme. Resolution capability is determined by solving hypersonic flow problems. From numerical and experimental results, it is concluded that the aerodynamic properties are dominated by the shock waves generated. It was found to be in agreement with the numerical and experimental results.