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Altitude-Wind-Tunnel Investigation of Combustion-Chamber Performance on J47 Turbojet Engine
From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."
Date:
December 15, 1950
Creator:
Campbell, Carl E.
System:
The UNT Digital Library