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Acoustic evaluation of a novel swept-rotor fanInlet noise and aerodynamic performance are presented for a high tip speed fan designed with rotor blade leading edge sweep that gives a subsonic component of inlet Mach number normal to the edge at all radii. The intent of the design was to minimize the generation of rotor leading edge shock waves thereby minimizing multiple pure tone noise. Sound power level and spectral comparisons are made with several high-speed fans of conventional design. Results show multiple pure tone noise at levels below those of some of the other fans and this noise was initiated at a higher tip speed. Aerodynamic performance of the fan did not meet design goals for this first build which applied conventional design procedures to the swept fan geometry.
Document ID
19780016954
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lucas, J. G.
(NASA Lewis Research Center Cleveland, OH, United States)
Woodward, R. P.
(NASA Lewis Research Center Cleveland, OH, United States)
Mackinnon, M. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1978
Subject Category
Acoustics
Report/Patent Number
NASA-TM-78878
AIAA PAPER 78-1121
E-9612
Meeting Information
Meeting: Fluid and Plasma Dyn. Conf.
Location: Seattle
Start Date: July 10, 1978
End Date: July 12, 1978
Sponsors: AIAA
Accession Number
78N24897
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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