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

Wallner, Lewis E., Saari, Martin J.
naca-rm-e8f10c
1948


Presents compressor and turbine performance characteristics at compressor-inlet ram-pressure ratio of 1.00, altitudes from 5000 to 35,000 feet, engine sppeds from 8000 to 13,000 rpm and turbine-inlet temperatures from 1400 degrees to 2100 degrees.

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http://naca.central.cranfield.ac.uk/reports/1948/naca-rm-e8f10c.pdf