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Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine. II - Engine PerformanceAn investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance characteristics of the X24C-4B turbojet engine over a range of simulated altitudes from 5000 to 45,000 feet,simulated flight Mach numbers from 0 to 1.08, and engine speeds from 4000 to 12,500 rpm. Performance data are presented to show graphically the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet. The performance data are generalized to show the applicability of methods used to determine performance at any altitude from data obtained at a given altitude. A complete tabulation of performance data, as well as lubrication- and fuel- system data, is presented.
Document ID
20050019258
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Meyer, Carl L. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Bloomer, Harry E. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 22, 2013
Publication Date
January 1, 1948
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-SE7L26
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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