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Cascade tests of serrated leading edge blading at high subsonic speedsCascade tests of two-dimensional fan rotor blade rows were performed to investigate the effects of leading edge serration on acoustic and aerodynamic performance. The test configurations covered a range of serration tooth geometries. Tests were performed to investigate effects of inlet air angle and velocity on performance. Aerodynamic performance was determined by flow surveys at the mid-span of the blade exit. Acoustic performance was determined by wake turbulence surveys and sound measurements in the semireverberent exhaust chamber. Measured acoustic and aerodynamic performance was comparable and indicated that a serration length of about six percent blade chord yields minimum noise generation and minimum total pressure losses.
Document ID
19750003911
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Smith, E. G. (General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1974
Publication Information
Publisher: NASA
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-2472
Accession Number
75N11983
Funding Number(s)
CONTRACT_GRANT: NAS2-5462
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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