火箭推进2026，Vol.52Issue(3)：13-24,12.DOI:10.3969/j.issn.1672-9374.2026.03.002
基于修正Kantrowitz准则的轴对称进气道逆向放气槽设计
Design of reverse bleed slot for axisymmetric inlet based on modified Kantrowitz criterion
摘要
Abstract
To address the lack of theoretical foundation in bleed design for hypersonic inlets and the overly conservative predictions of the traditional Kantrowitz criterion,a collaborative design method for reverse bleed slots incorporating a modified Kantrowitz criterion was proposed.Taking an axisymmetric inlet with a high internal contraction ratio and curved compression surface as the research object,numerical simulations were employed to systematically analyze the flow characteristics and self-starting performance under various bleed slot configurations.The results indicate that while the design based on the traditional Kantrowitz criterion enables the inlet to self-start at 3.35Ma,it still falls 4.3％short of the target 3.50Ma.In contrast,with the modified criterion,the self-starting Ma is increased to 3.51Ma under the condition of a 22.1％reduction in total compensation area,yielding a relative deviation of only 0.28％from the target value.Furthermore,under typical operating conditions,the design based on the modified criterion achieves lower bleed flow rates(below 0.7％),while key performance parameters such as the exit total pressure recovery coefficient remain nearly equivalent(approximately 0.58)for both designs.This indicates that the new method improves starting capability without compromising through-flow performance.This study provides a refined design approach for hypersonic inlet bleed systems characterized by a clear theoretical basis,high design accuracy,and low flow loss.关键词
高超声速进气道/起动性能/逆向放气槽/修正Kantrowitz准则/流动控制Key words
hypersonic inlet/starting performance/reverse bleed slot/Kantrowitz criterion/flow control分类
航空航天引用本文复制引用
杨潇,孙迪,李永洲,余文锋,赵胜海,胡杰华..基于修正Kantrowitz准则的轴对称进气道逆向放气槽设计[J].火箭推进,2026,52(3):13-24,12.基金项目
国家重点实验室基金(6142701210102) （6142701210102）
江西省研究生创新专项(YC2024-S629) （YC2024-S629）
江西省双千计划创新领军人才项目(CK202206068) （CK202206068）
航空科学基金(20240012056001). （20240012056001）
