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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。这些结果为RBCC发动机火箭引射模态工作过程的深入研究和性能优化提供了一定的理论依据
Based on the finite volume method of upwind finite element method, the flow field in the inlet / mixing section / combustor / tailpipe / rocket is numerically simulated based on the NS equations of rocket-based combined cycle (RBCC) The complex flow structure in the echelon flow channel is analyzed. The mechanism of the rocket emanation mode working process is discussed theoretically. The mixing performance of RBCC experimental model is discussed. Finally, the experimental results are compared with each other. These results provide a theoretical basis for further research and performance optimization of RBCC engine rocket ejector modal working process