固体火箭发动机喷管及羽流流场的数值分析

Numerical analysis of nozzle and plume flow field of a solid rocket motor

采用FLUENT流动计算软件对某空射型导弹发动机的喷管及羽流流场进行了一体化的数值仿真研究,分析了导弹飞行高度和马赫数对喷管羽流流动的影响。仿真结果与地面热试车观察到的结果相吻合,可为固体火箭发动机的研究开发提供参考。

The numerical simulation of the nozzle and plume flow field of a rocket motor launched from air was performed by using FLUENT software. The influences of flying altitude and Mach number on the plume flow were analyzed. The simulation results agree with the results observed from the test on the ground, and provide reference for solid rocket motor development.