3D simulation of a Hall-effect thuster near plume with a central cathode

This makes use of a hybrid particle-in-cell/fluid (PIC/fluid) formulation, and is here used to assess the 3D effects of the neutralizer position on the plasma properties in the near plume. The annular exit plane of the thruster coincides with the z = 0 plane, while the exit plane center-point is at x = y = z = 0.

This dataset refers to a simulation with a neutralizer located at the thruster center: x = y = z = 0. All shown results refer to the final simulation time (1.6 ms) and are time-averaged over periods of 0.2 ms.