Effect of Roughness in Jets in Mach 5 Cross Flow
Transverse jet injection into supersonic/hypersonic cross flow 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. These applications all involve complex three dimensional flow patterns comprising separated regions, shock waves, shear layers and wakes in common. Owing to numerous applications and these complicated flow features, transverse injections over different geometries and various forebodies have been received significant amount of interest. 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. Recent studies of missile/forebody applications involving reaction control jets by several researchers have investigated jet interaction phenomenon on various axisymmetric body configurations at supersonic/ hypersonic speeds [1, 2, 3, 4]. Their aim was to investigate control effectiveness of transverse/lateral jets on different missile body configurations.
KeywordsCross Flow Wall Pressure Separation Region Solid Rocket Motor Incoming Boundary Layer
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