Numerical simulation for non equilibrium chemically reacting fluid field of the solid rocket motor exhaust plume

In order to solve the problems of the non equilibrium chemically reacting numerical simulation for solid rocket motor exhaust plume with high temperature, fast speed and chemical reaction, this study started form the thermal calculation of solid rocket motor and one dimensional isentropic flow, and get the nozzle exit parameter and component content of the fuel gas. On the base of that, a control equation was established which including the transport equation, non equilibrium chemically reaction dynamic process and N-S equation. The control equation was solved with the finite volume method which based on the MUSCL ROE format. The results give out the flow field structure of the exhaust plume flow structure and the component distribution of jet flow, which build a study foundation for the protection of exhaust plume and the target feature.