摘要:
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。
Abstract:
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.
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