Supersonic inviscid flows in missile propulsive jet are simulated numerically with discontinuous finite element method based on twodimensional conservation laws, which is developed to solve axlsymmetric Euler equations. Computational results show good agreement with experimental data. The method shows higher resolution at discontinuous points compared with TVD schemes. It exhibits high capability in capturing shocks without numerical oscillation and artificial viscosity near discontinuous points.

When a shock wave propagates into a quiescent atmosphere of low pressure from a nozzle orifice, the flow can be simplied by solving a axisymmetric unsteady flow problem. In this paper second order accurate upwind schemes in total variation diminishing (TVD) type is employed for numerically simulating underexpanded supersonic free jet. A satisfactory time-dependent solution has been achieved.