数值模拟了火箭垂直发射燃气流场的非定常过程，在计算中采用了二阶精度的ＭＵＳＣＬ格式，在引入单调性限制条件和一定的耗散机制后，该方法适应于Ｅｕｌｅｒ坐标系下的计算。计算结果表明，该方法得到的流场激波结构十分清晰，计算结果和实验规律相一致。

The numerical results of burning gas flow during the vertical launch of a rocket are reported.The second order accurate MUSCL scheme is employed.The scheme is suitable for the calculation in Eulerian coordinates on monotonicity condition and some dissipation mechanisms are introduced.The computed results show that the shockwave structure in interaction flowfield is very clear and agrees well with that observation in experiments

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