空气动力学学报2011，Vol.29Issue(2)：135-141,7.
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
摘要
Abstract
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 wail, 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Key words
scramjet/ isolator/ shock train/ forced shock train oscillation/ wall pressure fluctuation分类
航空航天引用本文复制引用
曹学斌,张堃元..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[J].空气动力学学报,2011,29(2):135-141,7.基金项目
国家自然科学基金(10572059) （10572059）
