718 Flow and Supersonic Combustion Phenomena in Scramjet Engine by Using Shock Tunnel

Flow and combustion phenomena in a scramjet engine model were investigated by using a small high enthalpy shock tunnel. At Mach number about 6.5, double wedges were set in the test section as a scramjet engine intake and a combustion chamber model. Schlieren-image visualization and wall static pressure measurements were conducted. The compression process used the oblique shock system, which was generated by vehicle edge (fore-body) and cowl, was observed. H_2 and/or premixed C_2H_2-air mixture was injected normally to the supersonic cross flow in the combustion chamber model. To observe a self-emission from combustion gas, the high-speed video camera (18,000fps) with an image intensifier unit was used. The supersonic combustion in supersonic flowfield in the combustion chamber model was confirmed.