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提出了塞锥型面设计的特征线法及示例结果，得出了侧喷管粘性跨音速和超音速内流场数值计算结果，及塞锥外流和尾流的Ｅｕｌｅｒ 方程解，总结了塞式喷管工作特性的固体推进剂燃气模拟实验系统、实验结果及主要结论．塞式喷管火箭发动机是一个复杂而有挑战性的研究方向，对于发展新一代先进天地往返运输系统有重要作用．
The characteristic line method and the example results of the cone-cone profile design are presented. The numerical results of viscous transonic and supersonic flow field in the side nozzle and the solution of the Euler equation of the plug flow and the wake are obtained. Solid propellant gas simulation experimental system for nozzle operating characteristics, experimental results and main conclusions. Plug nozzle rocket motor is a complex and challenging research direction, for the development of a new generation of advanced world transportation system has an important role.