The flow field and thermal environment of gap in solid rocket nozzle were simulated by finite element method.
用有限元素法数值模拟了固体火箭发动机喷管内缝隙的流场和热环境。
Then, the experiment of flow separation in the nozzle was done with a solid rocket motor, and the inside pressure data along the axis of the nozzle was gotten.
然后，利用某型号固体火箭发动机进行喷管分离流试验，测得了喷管壁面上沿轴向的压强分布数据。
Numerical 3d simulation and research on inner nozzle and outlet flow field of solid rocket motor of long range missile designed by Russia using STAR-CD computational fluid software.
采用STAR - CD计算流体软件对某俄式发动机的喷管内流场及喷管出口处流场进行了三维的数值仿真与研究。
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