搭建了二维超-超引射器实验系统，进行了二次喉道型式引射器启动特性和负载特性实验，获得了引射器混合室内流场纹影图，结果表明：超声速引射器临界启动状态下，混合室内存在反压引起的激波系；引射器完全启动状态下，主激波系可始于混合室后段，无需被完全吞入二次喉道内；二次流对引射器启动有助推效果，可使混合室内激波系后移；一次流对二次流有压缩作用，且一次流工作压力越高，压缩作用越强；一次流、二次流之间会形成明显的混合层，当一次流、二次流静压不匹配时，一次流喷管出口内端壁处将形成较强斜激波，其在固壁与混合层之间反射、交叉，并向下游延伸，会降低一次流引射性能。

The test facility of 2-D supersonic-supersonic ejector was constructed. Varieties of tests were carried out to investigate the starting and load characteristics of a second throat ejector. The schlieren photographs of the mixing chamber flow field were got by schlieren apparatus synchronously. The experimental results show that there are shocks brought by background pressure in mixing chamber fore part while the ejector starts critically. It is possible that the main shocks originate from the mixing chamber rearward while the ejector starts completely. Secondary flow has booster action for ejector starting which can make shocks to move backward in evidence. As the secondary flow is injected, the mixing layer between primary and secondary flow will occur obviously. If the pressures of primary and secondary flow are not matched, a strong oblique shock wave will be formed at nozzle exit inwall, which will be reflected between the wall and mixing layer, then the capability of primary flow will be reduced.