二元高超声速进气道激波振荡特性实验  

Experimental Investigation on the Shock Wave Oscillation Behaviors in a Two-Dimensional Hypersonic Inlet Flow

作　　者：李祝飞[1] 高文智[1] 李鹏[1] 姜宏亮[1] 杨基明[1] 

机构地区：[1]中国科学技术大学

出　　处：《推进技术》2012年第5期676-682,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金(11132010)

摘　　要：通过在进气道/隔离段模型出口附近设置固定的堵塞楔块提高反压,并采用高速纹影拍摄同步壁面压强测量的手段,在马赫数5.9的激波风洞中研究了二元高超声速进气道在不同堵塞度下的流动特征。研究结果表明,在较低的堵塞度下,进气道仍然能够保持起动状态,而在较高的堵塞度下,进气道出现激波振荡。上游产生的压缩波/激波在节流段的反射是出现激波振荡的重要原因之一。随着堵塞度的增加,激波振荡的频率有所升高。A two-dimensional hypersonic inlet which exhibits self-starting characteristics was tested with different exit throttling ratios in shock tunnel at a freestream Mach number of 5.9 by applying simultaneously high speed schlieren imaging and surface pressure measurements. Results indicate that the backpressure generated from the throttling device can be tolerated and the inlet can maintain starting mode at low throttling ratios. Shock wave oscillations were observed and discussed in details when the inlet was operated at high exit throttling ratios. The upstream propagating normal shock in the duct during oscillation is related to the compression waves/shock waves that reflect at the throttling section. The oscillation frequency increases with increasing exit throttling ratio.

关 键 词：激波风洞 高超声速进气道 激波振荡 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]