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.
出处
《实验流体力学》
CAS
CSCD
北大核心
2013年第6期39-42,共4页
Journal of Experiments in Fluid Mechanics
关键词
进气道动态特性
Bump进气道
进
发匹配
流场畸变
inlet dynamic characteristic
bump inlet
inlet/engine compatibility
flow field distortion
作者简介
杨应凯（1964-），男，重庆人，研究员。研究方向：进气道设计与实验研究。
