Numerical Analysis of the Rarefied Plume from an Arcjet Thruster: Effect of the Nozzle Exit Shape

Abstract

The plume flow field of an arcjet thruster with hydrazine decomposed gas as the propellant has been numerically analyzed to reveal a backflow field, using Direct Simulation Monte Carlo (DSMC). Hydrazine decomposed gas is approximated by a mixture of gas composed of N2, H2, and H. Four different nozzle lip shapes have been prepared to investigate their effects on the backflow, and species existing in the backflow have also been examined. The present results of mass flux at various angles measured from the plume axis have been compared with experiments, and a qualitatively fairly good agreement has been obtained.