Coupled numerical simulation with N-S and DSMC on vacuum plume

Vacuum plume and its contamination are very difficult problems for the designers in astronautics. Due to the lack of efficient experimental and computational facilities, the research in this field advances slowly. A finite difference method for the N-S equation and DSMC methods applied to numerically simulate the vacuum plume of attitude controlling rocker motor nozzle. Vacuum plume parameters distribution which are in good accord with the flow physics was obtained. The present work provides a good reference to the design of attitude controlling rocket motor nozle. It is a good base of vacuum plume contamination study.