飞机快速俯仰机动下Bump进气道的动态特性研究  

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

作　　者：杨应凯[1] 

机构地区：[1]成都飞机设计研究所,成都610091

出　　处：《实验流体力学》2013年第6期39-42,共4页Journal of Experiments in Fluid Mechanics

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W、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Tu在整个过程中变化不大。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.

关 键 词：进气道动态特性 Bump进气道 进 发匹配 流场畸变 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]