An experimental study was made on a cylindrical scramjet combustor with a step using vitiated air. The stagnation temperature and the pressure of the vitiated air were 1000 K and 1.5 MPa, respectively. Simulated flight speed was Mach 4.4 at a simulated altitude of 20 km. Perpendicular injection showed better mixing performance than did parallel injection. As equivalence increased, supersonic combustion was switched to subsonic combustion. Mixing in the supersonic combustion mode was very slow compared with that in subsonic mode.
Experiment on a Cylindrical Scramjet Combustor. 1: Simulated Flight Mach Number of 4.4
1986
17 pages
Report
No indication
English
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