Motion pictures at camera speeds up to 3000 frames per second were taken of the combustion of liquid oxygen and gasoline in a 100-pound thrust rocket engine. The effect of seven methods of propellant injection on the uniformity of combustion was investigated. The flame front was generally found to extend to the injector faces and all the injection systems showed considerable nonuniformity of combustion. Pressure vibration records indicated combustion vibrations that corresponded to resonant-chamber frequencies.
Photographic Investigation of Combustion in a Two-dimensional Transparent Rocket Engine
1953-01-01
Miscellaneous
No indication
English
Photographic investigation of combustion in two-dimensional transparent rocket engine
Engineering Index Backfile | 1953
|Rocket engine nozzle photographic system
NTRS | 1968
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