Abstract
This paper presents flows and combustion phenomena in Scramjet engine model. Hypersonic flow was obtained by using a small high enthalpy shock tunnel. At Mach number of about 6.9, Scramjet engine model was set in the test section. At first, the oblique-shock compression process was studied. Gaseous Hydrogen was injected into the supersonic cross flow from intake wall. We conducted Shlieren-image visualization and wall static pressure measurements, self-emission observation. Shlieren-image visualization and self-emission were observed by using CCD camera. We verified the supersonic combustion and shock- induced combustion.
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