Abstract: A new computational method for plane steady supersonic flow with shock wave is developed. The differential equations and boundary conditions in new lagrangdan variables are formulated. We calculated a specific case that the equation of solid surface is a parabola y=(1)/(2)x².In this example, theshape of the shock wave is calculated. Before the formation of the shock wave,the flow has an exact solution.Our computational results coin-side well with the exact solution.