摘要
使用特征线方法数值模拟固体火箭发动机喷管内的二维流场，经过流场积分计算喷管推力。通过大量计算及数据处理，获得了流场内各流动参数的分布规律，以及几组综合关系曲线，应用这些曲线对流场特征进行分析研究从而实现最佳推力喷管型面设计。分析研究表明，这种数值计算能够比较真实地描述此种流动情况，具有较好的稳定性和通用性，计算结果可用于确定推力最大时的喷管扩张段最佳型面。
This paper discusses a method based on the theory of characterustics for the numerical simulation of two-dimensional,supersonic flow in nozzles and thereby obtaines the nozzle thrust with folw-field's integral.By way of a large number calculating and data processing ,the changing law of flow parameters is received,at the same time getting several curves of synthetic relations and achieving the diverging portion of optimum thrust nozzle contour.It is shown that the numerical calculation can simulate the nozzle flow relatively good and have quite good stability and interchangeablity .The results can be used to determine the optimum thrust nozzle contour.
