超声速和高超声速横向喷流数值模拟

推进技术 ›› 2005, Vol. 26 ›› Issue (5): 417-419.

超声速和高超声速横向喷流数值模拟

邓有奇,吴晓军,郑鸣,周乃春

北京航空航天大学航空科学与工程学院;北京100083;中国空气动力研究与发展中心;四川绵阳621000;中国空气动力研究与发展中心;四川绵阳621000;中国空气动力研究与发展中心;四川绵阳621000

发布日期:2021-08-15

Numerical simulation of supersonic and hypersonic jet interactions

School of Aeronautics Science and Technology,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China;China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China

Published:2021-08-15

摘要/Abstract

摘要： 为了解横向喷流的干扰影响和喷口附近的流场结构,采用分块对接网格和“O”型网格技术,数值求解N-S方程来模拟超声速和高超声速流场中横向喷流的干扰流场。对两种尖拱弹身外形的超声速和高超声速喷流干扰流场进行了数值计算,计算结果与风洞实验数据吻合一致。在此基础上,开展了某型导弹多喷构型干扰流场的数值模拟,得出一些横向喷流数值模拟的结论。

关键词: 横向喷流+;流动分布;数值仿真;有限体积法

Abstract: In order to understand the effects of lateral jet interaction and the structure of the flow field nearby the jet nozzle,the lateral jet interaction in supersonic and hypersonic flow was simulated numerically by solving the N-S equation with multi-block point matched grids and "O" type grid generation technique.The numerical simulation of the lateral jet interaction for finned bodies in the supersonic and hypersonic flow was performed.It is shown that the computational results are in good agreement with the experimental data.Based on this,numerical simulation of the jets interaction for missile is also presented.Some conclusions are made from the numerical simulation.

Key words: Lateral jet interaction~+;Flow distribution;Numerical simulation;Finite volume method

邓有奇,吴晓军,郑鸣,周乃春. 超声速和高超声速横向喷流数值模拟[J]. 推进技术, 2005, 26(5): 417-419.