Preliminary results of an altitude-wind-tunnel investigation of an axial-flow gas turbine-propeller engine V : combustion-chamber characteristics

Geisenheyner, Robert M., Berdysz, Joseph J.
naca-rm-e8f10d
1948


Presents combustion-chamber performance of axial-flow gas turbine-propeller at pressure altitudes from 5000 to 35,000 feet, compressor-inlet ram-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm as a function of corrected engine speed and corrected horsepower.

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