摘要
采用二维耦合隐式NS方程和标准kε-湍流模型,对采用Hark形头部的一体化高超声速飞行器在进气道关闭、发动机通流和发动机点火工况下的攻角特性进行了数值仿真研究.探索了可变攻角情况下,飞行器各部件对飞行器整体气动-推进性能的贡献程度.结果表明,在3种不同的工作状态下,飞行器都是纵向静稳定的,足够大的升阻比可以满足飞行器飞行要求,同时,对发动机型面及机身上壁面的改进有利于进一步满足飞行器对气动-推进性能的要求.
Two-dimension coupled implicit NS equations and standard k- epsilon viscous models were used to simulate the angle of attack characteristics of integrated hypersonic vehicle with hark head configuration under three kinds of working conditions, i.e. inlet cut-off, engine through-flow, engine ignition. The influence of each component on the aero-propulsive performance of vehicle was discussed. It is concluded that the longitudinal static stability of vehicle is good; it has enough lift-to- drag ratio to satisfy the flying requirement of the vehicle. At the same time, it is very important to change the configurations of engine and upper surface of airframe to improve the aero-propulsion of the vehicle.
出处
《应用数学和力学》
EI
CSCD
北大核心
2009年第6期725-732,共8页
Applied Mathematics and Mechanics
基金
国防科技大学优秀研究生创新资助项目(B070101)
湖南省研究生科研创新资助项目(3206)
关键词
一体化高超声速飞行器
攻角特性
部件分析
数值仿真
Hark形头部
气动-推进性能
integrated hypersonic vehicle
properties of attack angle
component analysis
computer simulation
Hark head configuration
aero-propulsive performance
