移动唇口变收缩比侧压式进气道反压特性和自起动性能  

Study on back pressure and self-starting characteristics for sidewall-compression inlet with variable internal contraction ratio by moving cowl

作　　者：潘瑾[1] 张堃元[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2009年第1期104-109,共6页Journal of Aerospace Power

基　　金：国家863计划(2003AA723020)

摘　　要：在来流马赫数为3.85条件下,开展了移动唇口可变收缩比侧压式进气道反压特性和自起动性能风洞实验.研究了不同内收缩比条件下,侧压式进气道抗反压性能和起动性能.实验结果表明:在正常工作条件下,侧压式进气道内收缩比大小影响其抗反压能力,内收缩比1.19的侧压式进气道能抗23.42倍反压,内收缩比1.24的侧压式进气道能抗26.44倍反压,内收缩比较大的进气道抗反压能力强;不能自起动的侧压式进气道,通过移动唇口减小其内收缩比,可以顺利实现自起动.An experimental study was performed at Mach 3.85 wind tunnel about back pressure and self-starting characteristics for sidewall- compression inlet with variable internal contraction ratio. The results show that, the internal contraction ratio has effects on back pressure characteristics of sidewall-compression inlet; the inlet with internal contraction ratio 1.19 can withstand a maximum back pressure of 23.42 times static pressure; the inlet with internal contraction ratio 1.24 can withstand a maximum back pressure of 26.44 times static pressure; The sidewall-compression inlet can realize self-starting by moving cowl backwards.

关 键 词：侧压式进气道 可变内收缩比 超声速 自起动 反压 风洞实验 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]