摘要
尾喷管构型的选取在高超音速飞行器一体化设计中有着举足轻重的作用。采用二维耦合隐式欧拉方程对高超音速飞行器内定常无粘流场进行了数值仿真,分析了尾喷管斜面倾角分别为8°、11°、13°和15°时,其构型对高超音速飞行器处于3种不同工作状态下(即进气道关闭、发动机通流和点火)纵向静稳定性的影响。结果表明,当尾喷管斜面倾角为11°时,高超音速飞行器的纵向静稳定特性较好,为下一步改型工作提供了参考。
It is significant for the integral design of hypersonic vehicle to select configuration of the tailpipe nozzle. The constant inviscid flow field in hypersonic vehicle was numerically simulated by using 2D coupled implicit Euler equations. When slope tilt angle of the tailpipe nozzle was 8°, 11°, 13°and 15°respectively, the effects of configuration of the tailpipe nozzle on the longitudinal static stability of hypersonic vehicle under three kinds of different working conditions （ such as inlet closedown, motor through-flow and ignition） were analyzed. The results show that the longitudinal static stability of hypersonic vehicle is better when slope tilt angle of the tailpipe nozzle is 11°, which can provide the reference for further modification.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2008年第4期310-312,320,共4页
Journal of Solid Rocket Technology
关键词
高超音速飞行器
尾喷管
纵向静稳定性
数值仿真
hypersonic vehicle
tailpipe nozzle
longitudinal static stability
numerical simulation
