Development and Validation of an MHD Code for Study of Argon plasma Flow Characteristics in the PFSB Thruster

Applying Roe’s scheme to solve the MHD equations leads to reduction of the numerical viscosity and growth of the accuracy. By increasing 2 dis I m ɺ in MPD thruster that accompanies strong expansion near the electrodes tips, Roe’s scheme has failed. In the zones where need more numerical viscosity, hybridizing Roe’s scheme with HLLE method provides a stable solution and limits the numerical viscosity in the other zones. To achieve a high-resolution method, new modification of MUSCL technique has been employed. This method is called OMUSCL2 technique which has lower dispersion and dissipation errors. For validation of developed algorithm, the Princetonfull-scale benchmark thruster, with cathode length of 7.62cm , mass flow rate of 6gr s and total discharge current of 15.3kA , has been simulated.The comparison of the predicted results of magnetic field and enclosed current with the measured data shows good qualitative and quantitative agreement.The calculated thrust is 52.67 N which showsabout6% difference compared with measured value. Furthermore, this simulation properly predicts the experimentally exhaust plume structure.