超燃冲压发动机隔离段非对称来流下激波串受迫振荡流动研究  

Experimental study of forced shock train in isolator under asymmetric incoming flow

作　　者：曹学斌[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,江苏南京210016

出　　处：《空气动力学学报》2011年第2期135-141,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(10572059)

摘　　要：用非对称马赫1.98的隔离段直连实验研究了不同波形不同频率的脉动反压对隔离段内流动的影响。实验结果表明:隔离段能有效地隔离不同频率不同波形周期性反压脉动对上游进气道的影响;反压脉动以第二特征波速向上游传播,但在激波振荡区域,压力脉动主要受激波振荡的影响;厚附面层一侧的下壁面激波振荡区域内压力脉动前传时以指数规律衰减,衰减的程度随着频率和波形的改变而改变。而薄附面层的上壁面激波振荡区域内压力脉动前传时不是单调下降,而是波动的。The Ma=1.98 experiment under asymmetric incoming flow was conducted to analyze the response of the wall pressure in an isolator when the shock train is subjected to a periodic motion at a low frequency.It was found that the isolator effectively isolates the periodic back pressures from the inlet.Wall pressure fluctuations are due to the propagation of wave fronts of the second acoustic mode.But they are subjected to an oscillating shock train in the most part of the shock oscillation region.Attenuation of wall pressure fluctuations in the shock oscillation region accords with the exponential law on the lower wall,and changes by wave shape and frequency of back pressure.It does not moronically decrease but fluctuate on the upper wall.

关 键 词：超燃冲压发动机 隔离段 激波串 激波受迫振荡 壁面压力脉动 

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]