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Forward sweep, low noise rotor bladeA forward-swept, low-noise rotor blade includes an inboard section, an aft-swept section, and a forward-swept outboard section. The rotor blade reduces the noise of rotorcraft, including both standard helicopters and advanced systems such as tiltrotors. The primary noise reduction feature is the forward sweep of the planform over a large portion of the outer blade radius. The rotor blade also includes an aft-swept section. The purpose of the aft-swept region is to provide a partial balance to pitching moments produced by the outboard forward-swept portion of the blade. The noise source showing maximum noise reduction is blade-vortex interaction (BVI) noise. Also reduced are thickness, noise, high speed impulsive noise, cabin vibration, and loading noise.
Document ID
19940032260
Acquisition Source
Headquarters
Document Type
Other - Patent Application
Authors
Brooks, Thomas F.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
May 2, 1994
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.71:LAR-14569-1
Patent Number: NASA-CASE-LAR-14569-1
Patent Application Number: US-PATENT-APPL-SN-238044
Report Number: NAS 1.71:LAR-14569-1
Accession Number
94N36767
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
NASA-CASE-LAR-14569-1
Patent Application
US-PATENT-APPL-SN-238044
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