Shock Induced Combustion and Flame Folding in Supersonic Combustion Ramjet Engine

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This research was primarily concerned with flows and combustion phenomena in Scramjet engine model. Hypersonic flow was obtained by using small high enthalpy shock tunnel. At Mach number of about 7, Scramjet engine model was set in the test section. At first, the oblique-shock compression process was studied. Gaseous H2 or He were injected with the injection angle of 70 degrees to the supersonic cross flow from intake wall. We conducted Schlieren-image visualization and wall static pressure measurements, self-emission observation. Schlieren-image visualization and self-emission were observed by using CCD camera and high-speed video camera. We verified the supersonic combustion and shock-induced combustion.And also, the evaluation of supersonic mixing was conducted by using catalytic reaction on platinum wire surface. This method was applied to evaluate the time variation of hydrogen concentration in the mixing layer. The results showed that the strength of the correlation between the time variations of the hydrogen concentration and velocity in the mixing layer was effected by mixing conditions.