航空学报2026，Vol.47Issue(7)：71-79,9.DOI:10.7527/S1000-6893.2025.32715
亚声速异形进气道小流量失稳特性
Low flow rate instability characteristics of a subsonic irregular inlet
摘要
Abstract
Irregular inlets can enhance the stealth capability of aircraft,but their complex flow structures may lead to instability under low flow rate conditions,thus affecting the normal operation of the engine.Numerical simulations are conducted to investigate the flow characteristics and performance behavior of an irregular inlet,with particular focus on its instability mechanism under throttled(low flow rate)conditions.The results indicate that under the high flow rate condition,local transonic regions appear within the duct,leading to a reduction in the total pressure recovery coeffi-cient,whereas under the low flow rate condition,the inlet boundary layer flow is subjected to a strong adverse pres-sure gradient near the throat,which induces boundary layer separation.The multiple vortex structures within the inter-nal duct cross-section gradually merge into a single vortex structure,significantly increasing the total pressure loss and posing challenges for engine matching.Furthermore,the angle of attack has a pronounced impact on the inlet's sta-bility boundary.At positive angles of attack,separation is more likely to occur on the lower wall of the first bend and the upper wall downstream of the bulge,leading to an earlier onset of flow instability and increased sensitivity of inlet performance to flow disturbances.This study clarifies the core physical mechanisms responsible for low-flow-rate insta-bility in shaped inlets and provides theoretical guidance for robust inlet design and stability management under complex operating conditions.关键词
异形进气道/小流量状态/亚声速/内流特征/失稳机制Key words
irregular inlets/low flow rate conditions/subsonic/internal flow characteristic/instability mechanism分类
航空航天引用本文复制引用
王博仪,王利敏,王立波,谭慧俊,汪昆..亚声速异形进气道小流量失稳特性[J].航空学报,2026,47(7):71-79,9.基金项目
国家自然科学基金(12025202) National Natural Science Foundation of China(12025202) （12025202）
