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Analytical parametric investigation of low pressure ratio fan noiseThe results of an analytical study are reported which shows the effect of various physical and operating parameters on noise produced by low pressure ratio propulsive fans operating at subsonic top speeds. Acoustical duct lining effects are included in the study. The concepts used to develop the noise theory used in the study, as well as the correlation between the theory and model test results are also presented. It is shown that good correlation has been established between theory and experiment. Using the theory, it is shown that good aerodynamic design, maximum acceptable fan solidity, low tip speed operation and use of few blades and vanes leads to the lowest noise levels. Typical results of the study indicate that a fan operating at 1.2 fan pressure ratio and 700 ft/second tip speed with 12 blades and 7 vanes and including modest acoustic treatment on the duct wall would produce levels allowing a 100,000 lb. STOL aircraft to meet a noise level objective of 95 PNdB at 500 ft at takeoff.
Document ID
19730009284
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Metzger, F. B.
(Hamilton Standard Windsor Locks, CT, United States)
Hanson, D. B.
(Hamilton Standard Windsor Locks, CT, United States)
Menthe, R. W.
(Hamilton Standard Windsor Locks, CT, United States)
Towle, G. B.
(Hamilton Standard Windsor Locks, CT, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1973
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
HSER-5990
NASA-CR-2188
Accession Number
73N18011
Funding Number(s)
CONTRACT_GRANT: NAS1-10896
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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