固体火箭技术2025，Vol.48Issue(5)：763-771,9.DOI:10.7673/j.issn.1006-2793.2025.05.015
一种宽速域二元曲面压缩可调进气道设计
A wide-speed two-dimensional curved surface compression adjustable inlet design
朱永志 1匡正 1母忠强 2郭丽强 2袁化成1
作者信息
- 1. 南京航空航天大学 能源与动力学院,南京 210016
- 2. 北京流体动力科学研究中心,北京 100089
- 折叠
摘要
Abstract
To address the low outlet performance at the critical state(modal transition point)and the flow-through state(cruise point)of the inlet,an aerodynamic design study was conducted for a hypersonic mixed-compression two-dimensional variable-geome-try inlet integrating isentropic surface compression with wedge compression.The inlet capture area was determined based on mass flow requirements,and a full-speed-domain variable-geometry scheme was developed with Ma=5.5 as the design point.Building on this scheme,the total pressure recovery coefficient was enhanced by increasing the total contraction ratio through geometric variation.Results indicate that as the total contraction ratio increases,the inlet throat Mach number continuously decreases under both typical operating conditions,with the reduction magnitude proportional to the increase in total contraction ratio,while all inlet performance parameters exhibit nonlinear variations.For the critical state at Ma=3.5,the outlet Mach number remain around 2.5 across the inves-tigated total contraction ratios,achieving optimal performance at a total contraction ratio of 7.14.For the flow-through state at Ma=6.0,the outlet Mach number increases proportionally with the total contraction ratio,reaching optimal performance at total con-traction ratio 5.71.Mach number of the throat is reduced through variable geometry to minimize post-throat flow losses,and imple-menting boundary layer control measures such as shoulder bleed,shock wave/boundary layer interactions are mitigated.This signifi-cantly broaden the inlet's operational range and substantially enhanced its back-pressure tolerance,yielding a critical total pressure recovery of 0.827 at Ma=3.0 and a total pressure recovery of 0.341 at Ma=6.0.关键词
高超声速/二元进气道/变几何/宽速域/宽空域Key words
hypersonic/two-dimensional inlet/variable geometry/wide speed domain/wide airspace分类
航空航天引用本文复制引用
朱永志,匡正,母忠强,郭丽强,袁化成..一种宽速域二元曲面压缩可调进气道设计[J].固体火箭技术,2025,48(5):763-771,9.
