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Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller EngineAn altitude-wind-tunnel investigation of a TG-100A gas turbine-propeller engine was performed. Pressure and temperature data were obtained at altitudes from 5000 to 35000 feet, compressor inlet ram-pressure ratios from 1.00 to 1.17, and engine speeds from 800 to 13000 rpm. The effect of engine speed, shaft horsepower, and compressor-inlet ram-pressure ratio on pressure and temperature distribution at each measuring station are presented graphically.
Document ID
20030064137
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Geisenheyner, Robert M. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Berdysz, Joseph J. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
November 13, 1947
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E7J02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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