侧压式进气道动态攻角特性的风洞实验  

Experiments of sidewall compression scramjet inlet on dynamic characteristic of angle-of-attack

作　　者：刘凯礼[1] 张堃元[1] 郭斌[2] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航天科技集团公司中国航天空气动力技术研究院,北京100074

出　　处：《航空动力学报》2011年第8期1794-1800,共7页Journal of Aerospace Power

摘　　要：为了研究攻角导致的来流条件非定常变化对高超声速进气道性能的影响，以一个设计马赫数为6的侧压式进气道为研究对象，结合数值模拟的方法，在马赫数为3．85条件下进行了攻角动态变化的风洞实验，攻角变化范围为0°～8．2°，最大频率达到10．4Hz．研究结果表明：工作在大攻角时，侧压式进气道出现不起动现象，流场特征出现很大变化；攻角动态变化时，进气道重复出现起动一不起动再起动现象，由于受到壁面运动的影响，壁面点压力随攻角的变化曲线出现一定的迟滞现象，这在不起动时尤为明显；当进气道攻角动态频率增加时，进气道不起动时的攻角逐渐增加，而再起动时的攻角逐渐减小．In order to research the influence of dynamic angle-of-attack on the performance of hypersonic inlet, wind tunnel experiments were conducted on a sidewall compression scramjet inlet with Ma = 3.85, range of angle-of-attack 0°-8.2° and frequency up to 10.4 Hz. The present work suggests that： with the high angle of-attack, the inlet could work in unstart mode, and flow field features are significantly altered and also analyzed by a computational fluid dynamics （CFD） solver. In the dynamic process of angle-of-attack, the inlet could go through a start unstart-restart process hut the pressure on the wall has the hysteresis effect, especially when the inlet is unstart. With the rise of frequency, the value of unstarting angle-of-attack could increase and restarting value could decrease in the oscillation.

关 键 词：高超声速进气道 不起动 风洞实验 攻角动态变化 非定常流动 

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]