多喷管火箭发动机尾流场流动与辐射特性的数值模拟分析

采用k-ε湍流模型和离散坐标模型（discreteordinatesmethod，DO模型），使用CFD技术对4喷管火箭发动机的尾流场进行3-D数值模拟，研究了不同飞行高度和不同喷管均布直径的情况下尾流的流动特性和尾流对火箭底部的辐射特性。结果显示飞行高度对火箭底部的辐射热流密度有很大影响：飞行高度增加时，尾流边界逐渐变宽、变长；喷管之间距离缩小时，尾流增长，火箭底部辐射热流密度增大，高温区域增大。研究结果对多喷管火箭的总体设计有一定的指导价值。

Numerical Simulation on Plume Field and Radiation Characteristics of Multi-nozzle rocket motor

This paper focuses on researching the flowage characteristics of flow and the radiation characteristics of flow to the bottom of the rocket in the case of different height of fly and average diameter of nozzle. The author adopts k-ε Turbulence Method and Discrete Ordinates Method and CFD technique to do 3-D Numerical Simulation for plume field of the rocket engine with four nozzles. The result showed that the verge of flow became wider and longer when the height of fly increased, the flow became longer when the distance between nozzles became shorter. The height of fly had a great impact on density of radiation heat flow in the bottom of the rocket. When the distance between nozzles became shorter, density of radiation heat flow in the bottom of the rocket increased and high temperature area became larger. The research result had been of great value for the whole design of multi-nozzle rocket.