At present, micro satellites and small satellites are under rapid development. The pulsed plasma thruster is a good choice for its propellant system. For space application, the flume is in a great need to be studied. In this paper, DSMC(Direct Simulation Monte Carlo)/PIC (Particle in Cell) fluid hybrid method and one dimension MHD discharge model are used to simulate the NASA Glenn PPT flume from end to end. The distribution of deflection angle at the thruster outlet is achieved by calculation and comparison between experimental results. The results show that the deflection angle at the thruster outlet can improve the diffusion of flume, thus making an important factor influencing the simulation results.