A solid rocket motor with four nozzles is taken as the research object. According to its actual flight environment and the simulation boundary conditions are given. Then, the integrated simulation of nozzle-flow field in exhaust plume of solid rocket motor is carried out by means of FLUENT. The velocity of flow field in exhaust plume, temperature, and pressure are obtained. The simulation results are in good agreement with the actual flow conditions and the existence of Mach disk is proved.
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