摘要
为研究低速引射对高超声速飞行器气动加热的影响,对高超声速来流条件下大面积平板引射进行数值模拟,讨论了引射孔结构、迎角和引射入口速度对边界层流场的影响,得到了不同引射孔结构下壁面热流,引射影响因子及流动参数随引射入口速度的变化。结果表明:低速气体引射在一定程度上能缓解引射区域壁面和下游壁面的气动加热情况。4种引射状态中引射孔结构4(即面引射)壁面热流最低,其他3种引射孔结构冷却效果基本相当。相同条件下10°迎角低速气体引射降热效果明显优于0°迎角的情况。引射入口速度v=20 m/s时,0°迎角情况下,引射区引射影响因子约为0.23,即壁面平均热流降低约23%;10°迎角情况下,引射区引射影响因子约为0.45,约为0°迎角情况的2倍。
To study the impact of low speed ejection on aerodynamic heating of hypersonic aircrafts,the flat injecting of large area under hypersonic flow condition is numerical simulated in this paper.The influence of ejecting pore structure,incidence angle and injecting inlet velocity on boundary layer flow field are discussed.Wall heat flux under different ejecting pore structures variation of ejecting factors and flow parameters with inlet velocity are obtained.The results show that low speed gas ejecting can relieve the aerodynamic heating situation of injecting regional wall and the downstream wall to some extent.The bigger the inlet velocity,the better the thermal reduction will be.As for four ejecting pore structures the wall heat flux is the lowest in ejecting pore structure 4(surface ejecting pore structure),the other three ejecting cooling effect are basically quite.The thermal reduction of angle of attackα=10°is obviously better than the state ofα=0°.When injecting inlet velocity is 20 m/s,the injecting factor of injecting area is about 0.23,which means the averaged wall heat flux decreases about 23%underα=0°.And the injecting factor of injecting area is about 0.45 which is about double of the value ofα=0°.
作者
王丽燕
檀妹静
王振峰
聂春生
李宇
郑宇
WANG Liyan;TAN Meijing;WANG Zhenfeng;NIE Chunsheng;LI Yu;ZHENG Yu(Science and Technology on Space Physics Laboratory,China Academy of Launch Vehicle Technology,Beijing,100076,China)
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2019年第4期503-511,共9页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家安全重大基础研究(613285)资助项目
中央军委科学技术委员会基础加强类(0327004)资助项目
