机身头部构型对高超声速飞行器气动-推进性能的影响  

Influence of head configuration on aerodynamic-propulsive performance of hypersonic vehicles

作　　者：黄伟[1] 柳军[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2009年第4期369-372,378,共5页Journal of Solid Rocket Technology

基　　金：国防科技大学优秀研究生创新资助项目(B070101)

摘　　要：采用二维耦合隐式欧拉方程和标准k-ε湍流模型,对高超声速飞行器内外流场进行了数值仿真研究。离散采用二阶迎风格式,在考虑粘性影响的前提下,对飞行器机身头部进行了改型研究。分析了机身头部长细比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3种不同的工作状态下气动-推进性能的影响。结果表明,当飞行器机身头部长细比较大时,飞行器的气动-推进性能较好,为下一步的改进工作提供了参考。Two-dimension coupled implicit Euler equations and standard k-6 tubulent viscid models are introduced to simulate the flow of hypersonic vehicle, and the equations were discretized in second order upwind mode. On the basis of considering the viscous effect, the influence of head configuration on the aerodynamic-propulsive performance of hypersonic vehicle in three different working conditions i.e. close dinlet, open inlet with motor unfired and open inlet with motor fired were discussed. Results show that when the slenderness ratio of head is bigger, the aero dynamic-propulsive performance of vehicle is better.

关 键 词：高超声速飞行器 长细比 机身头部 气动-推进性能 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]