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Investigation of X24C-2 10-Stage Axial-Flow CompressorEffect of inlet-air pressure and temperature on the performance of the X24-2 10-Stage Axial-Flow Compressor from the X24C-2 turbojet engine was evaluated. Speeds of 80, 89, and 100 percent of equivalent design speed with inlet-air pressures of 6 and 12 inches of mercury absolute and inlet-air temperaures of approximately 538 degrees, 459 degrees,and 419 degrees R ( 79 degrees, 0 degrees, and minus 40 degrees F). Results were compared with prior investigations.
Document ID
20030064192
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Finger, Harold B. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Schum, Harold J. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Buckner, Howard Jr. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
August 21, 1947
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E7H22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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