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Matching Characteristics of J35-A-23 Compressor and Two-stage TurbineComponent data on the J35-A-23 compressor and two-stage turbine were used to determine the problems in matching the two units for operatio n in a turbojet engine. Possible operating regions were determined an d an equilibrium operating line was also determined for the assumed c onditions of zero flight speed and a jet nozzle area approximately 5. 5 percent greater than the wide-open nozzle area.
Document ID
20090025452
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Dugan, James F., Jr. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Rebeske, John J., Jr. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Finger, Harold B. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
August 6, 1951
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E51H15
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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