关键词: 火箭发动机喷管;等熵流;特性线法

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