飞机快速俯仰机动下Bump进气道的动态特性研究

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a〉10°时，上仰过程中，进道总压恢复系数口、出口总压综合畸变w、出口总压周向畸变△σ0降低，下俯过程中则升高．且上仰过程中L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Tu在整个过程中变化不大。

The study on bump inlet dynamic characteristics under aircraft fast pitching maneuver

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, at a〉10°, under up pitching, inlet total pressure recovery coefficient a, integrated total pressure distortion of inlet W,inlet total pressure circumferential distortion△σ0, 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.