An implicit upwind finite volume scheme wihch combines a kind of very simple flux splitting with a modified numerical flux method of second order accurate TVD scheme is presented in this paper using this method, we performed numerical simulation for the supersonic inviscid steady flow past an asymmetric three-dimensional body based on unsteady gasdynamics Euler's equations. The numerical results show this method has high resolution for discontinuity and is time-saving.

A method which Combines the numerical flux of high accurate TVD scheme with multistage method in time approaching is developed to calculate the problems of 2-D steady flow. Some special treatments are given to accelerate convergency. The numerical results of transonic flow over NAGA 0012 airfoil are obtained by this method. They show that this method is high accurate, of high resolut-ion nd time-saving.