An experimental study was made on supersonic mode combustors of an air breathing rocket engine. Supersonic streams of room-temperature air and hot fuel-rich rocket exhaust were coaxially mixed and burned in a conically diverging duct of 2 degrees half-angle. The effect of air inlet Mach number and excess air ratio was investigated. Axial wall pressure distribution was measured to calculate one dimensional change of Mach number and stagnation temperature.
Study of Air Breathing Rockets (III): Supersonic Mode Combusters
1983
22 pages
Report
No indication
English
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