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Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor. III - Effect on Over-All Performance Characteristics on Increasing Stator-Blade Angles in Inlet StagesThe stator-blade angles in the first four stages of a 16-stage axial-flow compressor were increased in order to decrease the angles of attack of these stages, and thereby to improve part-speed performance. The performance of this modified compressor was compared with that of the same compressor with original blade angles.
Document ID
20090025260
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Medeiros, Arthur A. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Hatch, James E. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
February 15, 1952
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-RM-E52B15
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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