Preliminary results of an altitude-wind-tunnel investigation of an axial-flow gas turbine-propeller engine I : performance characteristics

Saari, Martin J., Wallner, Lewis E.
naca-rm-e8f10
1948


Performance of a turbine-propeller engine equipped with an axial-flow compressor for engine speeds from 8000 to 13,000 rpm, at altitudes from 500 to 35,000 feet and compressor-inlet ram-pressure ratios from 1.00 to 1.17 is presented.

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