Experimental Investigation of Transverse Injection Flowfield at Mach 5 and the Influence of Impinging Shock Wave

摘要

Transverse jet injection into supersonic/hypersonic cross flows, which has been encountered in many engineering applications ranging from scramjet combustors and solid rocket motor or liquid engine thrust vector control systems to high speed flying vehicle reaction control jets, is comprised of complex three dimensional flow patterns including separated regions, shock waves, shear layers and wakes in common. The flowfield has received significant amount of interest since 60's. Earlier studies were focused on wind tunnel experiments and the utilisation of conventional measurement techniques such as Schlieren/Shadowgraph photography, wall pressure and concentration measurements to better understand the jet interaction and penetration phenomena-. These studies aimed to assess the effect of injection pressure ratio, location of injection and state of incoming boundary layer and type of injectant gas on jets in supersonic/hypersonic cross flow.