摘要
采用二维耦合隐式欧拉方程对高超声速飞行器内定常无粘流场进行了数值仿真,离散采用二阶迎风格式,分析了尾喷管倾角为8°、11°、13°和15°时,对高超声速飞行器分别处于进气道关闭、发动机通流以及发动机点火三种不同的工作状态下性能的影响。结果表明当尾喷管倾角为11°时,飞行器的升力特性、阻力特性和俯仰力矩性能得到了较好的权衡,性能得到了较大的提高,为下一步的改进工作提供了参考。
Two-dimension coupled implicit Euler equations were introduced to simulate the constant inviscid flow of hypersonic vehicle, and the equations were discretized by the second order upwind. When the deflection angle of afterbody nozzle was 8 degree, 11 degree, 13 degree and 15 degree respectively, the configuration of afterbody nozzle influencing on the performance of hypersonic vehicle in three different working conditions including inlet closed, inlet open but unfired, inlet open and fired were discussed. The conclusion is that when the deflection angle of afterbody nozzle is 11 degree, the lift characteristic, the drag characteristic and the pitching moment characteristic of the hypersonic vehicle is balanced better, and the performance of the hypersonic vehicle is improved, it can be referable for the following deign job.
出处
《弹箭与制导学报》
CSCD
北大核心
2008年第4期161-164,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国防科技大学优秀研究生创新基金资助
关键词
高超声速飞行器
尾喷管
升力特性
阻力特性
俯仰力矩特性
hypersonic vehicle
afterbody nozzle
lift characteristic
drag characteristic
pirching moment characteristic
