A numerical code is described that simulates the plumes of electric propulsion engines including ion thrusters and stationary plasma thrusters. In the present study, computed flow field results are compared to existing experimental measurements for the UK-10 ion thruster. The experimental measurements consist of ion flux, ion density, and floating potential data. The numerical code combines the direct simulation Monte Carlo method for modeling collisions with the Particle-in-Cell method for modeling plasma dynamics. Xenon neutrals and ions are modeled directly using particles. Electrons are described by the Boltzmann relation. The effect of a finite back pressure experienced in laboratory experiments is included. Agreement between simulation and experiment is satisfactory. The simulation results are found to be very sensitive to input conditions assumed at the thruster exit plane. In particular, there is uncertainty in specifying the effects of the curvature of the dished grids of the UK-10 thruster on the ion exit velocity profile.
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