火箭基组合循环发动机引射模态流动分析

Flow analysis and validation of rocket ejector mode for rocket based combined cycle

应用迎风格式有限体积方法求解N S方程的基础上 ,数值模拟了火箭基组合循环 (RBCC)发动机引射模态进气道 /混合段 /燃烧室 /尾喷管 /引射火箭内的流动过程 ,分析了引射模态流道中的复杂流动结构 ,从理论上探讨了火箭引射模态工作过程机理 ,讨论了RBCC实验模型的混合性能 ,最后与实验结果进行了比较 ,二者吻合较好。

Upwind scheme limited volume methodology was employed to solve Navier Stockes equation,the flow field in the inlet/mixer/combustor/nozzle/ejector rocket of a RBCC test model was simulated,the sophisticated flow structure in the duct was analysized,the principle of rocket ejector pumping and mixing ability of the model was discussed,and finally,the calculation was validated by the experimentation with good agreement each other All this results provide some theoretical basis for the deep research about RBCC ejector mode operation and parameter optimization