火箭推进2025，Vol.51Issue(2)：52-61,10.DOI:10.3969/j.issn.1672-9374.2025.02.006
考虑机身前体影响的S弯进气道大迎角性能试验
Experiment of S-shaped inlet performance at high angle of attack with the chined forebody considered
全景阁 1韩珊珊 1冯晓强 1郁新华 2孙琰1
作者信息
- 1. 西安航天动力研究所,陕西 西安 710100||西安市高速飞行器攻防对抗技术及应用重点实验室,陕西 西安 710100
- 2. 西北工业大学365 研究所,陕西 西安 710075
- 折叠
摘要
Abstract
Considering the influence of the chined forebody,an experimental investigation of a top-mounted S-shaped inlet for a high-maneuverable and stealth unmanned aircraft at high angle of attack is conducted.As the various parameters,such as the mass flow coefficient,mach number,angle of attack and slide angle,are studied comprehensively to obtain the aerodynamic characteristics of the inlet in subsonic and transonic flow,the work focuses on the influence of the chined forebody on the S-shaped inlet performance at high angle of attack.It is found that the chined forebody has an important positive effect on the performance of the S-shaped inlet at high angle of attack,due to the leading-edge vortex present.With the chined forebody considered,the performance of the S-shaped inlet at high angle of attack is improved,showing a different changing pattern compared with the general S-shaped inlet.As the angle of attack increases and is beyond a critical angle of attack,the total pressure recovery coefficient does not decrease any more but increases,and the distortion index doesn't reduce either.The inlet performance at high angle of attack is no longer getting worse but better,which is quite different from the general performance of S-shaped inlet.Moreover,the bad effect of the slide angle on the inlet performance reduces,and the inlet still can perform well at high angle of attack in small slide angle state.关键词
融合体前机身/前体分离涡/S弯进气道/大迎角/总压恢复系数/畸变指数Key words
chined forebody/leading-edge separated vortex/S-shaped inlet/high angle of attack/total pressure recovery coefficient/distortion index引用本文复制引用
全景阁,韩珊珊,冯晓强,郁新华,孙琰..考虑机身前体影响的S弯进气道大迎角性能试验[J].火箭推进,2025,51(2):52-61,10.
