攻角动态变化的侧压式进气道风洞实验  

Wind tunnel experiment of sidewall compression inlet with adjustable attack angle

作　　者：郭斌[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7期1601-1605,共5页Journal of Aerospace Power

摘　　要：在Ma=3.85的风洞中,对一个设计Ma=6起动Ma=2.5的侧压式进气道完成了攻角从0°→8°→0°的连续吹风实验.实验结果表明:0°攻角时进气道顺利起动,当攻角增大到5.7°时,进气道出现不起动;之后在8°到0°的变化过程中,在5.4°时又恢复了起动.另外,随着攻角的增加,流量系数在起动状态下缓慢减小,在不起动状态下急剧减小.实验中还进行了攻角0°→4°→0°的动态连续吹风实验,进气道全程都处于起动状态.This paper conducted a wind tunnel experiment at Ma=3.85,during which a continual blowing process was finished at the sidewall compression inlet with designed Ma=6 and starting Ma=2.5,when attack angle changed from 0° to 8°,and again to 0°.Experimental results show that,in the case of Ma=3.85,attack angle=0°,the inlet starts smoothly,and the pressure distribution is consistent with numerical simulation to a large degree.In the dynamic process of attack angle changing from 0° to 8°,when it increases to 5.7°,...

关 键 词：侧压式进气道 攻角可调 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]