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反向喷流是改变钝体迎风面压力和温度分布的有效手段之一，所以了解反向喷流流场对再入体防热及减阻设计具有重要意义。本文用有限差分法求解轴对称Ｎ－Ｓ方程模拟了球柱体头部反向喷流与超声速自由来流的干扰流场。研究了喷流出口压力对流场的影响。物面压力分布及喷流Ｍａｃｈ盘、弓形激波的脱体距离与实验值进行了比较，取得了一致的结果，喷流附近分离区的再附位置及再附产生的激波位置也与实验相符，但高压比下再附激波略强于实验。
Reverse jet flow is one of the effective methods to change the pressure and temperature distribution on the bluff body windward surface. Therefore, it is of great importance to know the reverse jet flow field on the heat resistance and drag reduction design of reentrant body. In this paper, the finite difference method is used to solve the axisymmetric N-S equation to simulate the interference flow field between the head reverse jet and the supersonic free flow. The influence of jet outlet pressure on the flow field was studied. The surface pressure distribution and jet Mach flow and bow shock separation distance were compared with the experimental data. The consistent results were obtained. The reattachment of the separation zone near the jet flow and the re-attachment of the shock wave were also compared with the experiment However, the reattached shock wave was slightly stronger than that under high pressure.