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Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet EngineAn investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust axial flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Engine operating range, acceleration, deceleration, starting, altitude, and flight Mach number compensation of the fuel control system, and operation of the lubrication system at high and low ambient air temperatures were evaluated.
Document ID
20030063990
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Hawkins, W. Kent (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Meyer, Carl L. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
August 23, 1948
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E8B19a
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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