CAJ | 학술논문

对两侧 Bump 进气道进行了动态特性风洞试验研究。研究表明：飞机做俯仰机动时，进气道相关性能参数随着时间作周期性变化；迎角α＞10°时，上仰过程中，进道总压恢复系数σ、出口总压综合畸变犠、出口总压周向畸变Δσ0降低，下俯过程中则升高，且上仰过程中上述参数值明显小于下俯过程，一个俯仰周期形成一个闭合环路；进气道出口总压脉动平均紊流度犜狌在整个过程中变化不大。
대량측 Bump 진기도진행료동태특성풍동시험연구。연구표명：비궤주부앙궤동시，진기도상관성능삼수수착시간작주기성변화；영각α＞10°시，상앙과정중，진도총압회복계수σ、출구총압종합기변희、출구총압주향기변Δσ0강저，하부과정중칙승고，차상앙과정중상술삼수치명현소우하부과정，일개부앙주기형성일개폐합배로；진기도출구총압맥동평균문류도돈성재정개과정중변화불대。
The Bump inlet dynamic characteristics wind tunnel test is introduced.When air-craft pitching maneuver ,the bump inlet performance parameters show periodic change with time, atα>10°,under up pitching,inlet total pressure recovery coefficientσ,integrated total pressure distortion of inlet W ,inlet total pressure circumferential distortion Δσ0 reduce,under down pitch-ing,the above parameters increase,which are less than those under up pitching,and for a pitch period to form a close loop.The inlet total pressure pulsation average turbulence Tu change little in the process.