Description: Report presenting a study of the altitude-starting limits of a production turbojet engine with an axial-flow compressor and a multiple through-flow combustor. The ignition limits, flame-propagation limits, and acceleration limits of the engine were improved to increase the starting limits to relatively high altitude.
Date: October 29, 1952
Creator: Armstrong, John C. & Wilsted, H. D.
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Partner: UNT Libraries Government Documents Department