Abstract: This paper presents a method of two-dimensional characteristic which can be applied to the calculation and design of a rocket supersonic nozzle.Some useful conclusions are drawn from the analysis of computational results.The results,brought about by the method are so good that the method can be suggested as a reference for nozzle design and heat transfer analysis of rocket nozzle.

Key words: Rocket engine nozzle;Isentropic flow;Characteristic method

摘要： 本文介绍了用于计算超音速火箭喷管特性线方法.从基本原理、几个问题的处理到计算结果的分析和处理,得到某些有益的结果,可供喷管设计和喷管受热分析参考.

关键词: 火箭发动机喷管;等熵流;特性线法