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。 By setting a fixed block wedge near the exit of the inlet / isolation section to increase the backpressure and using high speed profiling to synchronize the wall pressure measurement, the binary hypersonic velocity Flow Characteristics of Intake Ports at Different Plugging Degrees. The results show that, at lower plugging degree, the inlet can still maintain the starting condition, while at higher plugging degree, the inlet oscillates shock. The upstream compression / shock reflection in the throttle section is one of the important reasons for shock oscillation. As the jamming degree increases, the frequency of shock oscillation increases.