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Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller EngineA preliminary investigation of an axial-flow gas turbine-propeller engine was conduxted. Performance data were obtained for engine speeds from 8000 to 13,000 rpm and altitudes from 5000 to 35,000 feet and compressor inlet ram pressure ratios from 1.00 to 1.17.
Document ID
20030065298
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Saari, Martin J. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Wallner, Lewis E. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
August 2, 1948
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E8F10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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