Preliminary results of an altitude-wind-tunnel investigation of an axial-flow gas turbine-propeller engine III : pressure and temperature distributions

Geisenheyner, Robert M., Berdysz, Joseph J.
naca-rm-e8f10b
1948


Pressure and temperature distributions throughout the TG-100A gas turbine-propeller engine were obtained at altitudes from 5000 to 35,000 feet, compressor-inlet ram-pressure ratios from 1.00 to 1.17, and engine speeds from 8000 to 13,000 rpm.

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