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从曲线坐标下的完全气体 N-S方程出发 ,采用 ENO差分格式 ,对点火发动机工作初期 ,在固体火箭发动机内腔形成的受限冷喷流流场进行数值模拟 ;在此基础上 ,分析了喷流的流场结构及特性。
Based on the complete gas NS equation under the curve coordinates, the ENO difference scheme was used to simulate the flow field of the restricted cold jet formed in the cavity of the solid rocket engine at the initial stage of ignition engine operation. On this basis, the jet flow The flow field structure and characteristics.