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Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine: Analysis of Combustion-Chamber Performance - 3Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were determined. Data are presented for a range of simulated altitudes from 15,000 to 45,0000 feet and a range of Mach numbers from 0.23 to 1.05 for various modifications of the engine.
Document ID
20030064136
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Campbell, Carl E. (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-E8B19
Report Number: NACA-RM-E8B19
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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