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Helicopter rotor blades

descriptionPublicationkeyboard_double_arrow_right Article , Journal 01 Dec 1993 English Publisher:Acoustical Society of America (ASA)Journal:The Journal of the Acoustical Society of America, volume 94, pages 3,536-3,536 (issn: 0001-4966, eissn: 1520-8524, Copyright policy )
Authors: Frederick J. Perry; Alan Brocklehurst;

doi: 10.1121/1.407147

Helicopter rotor blades

Abstract

Flow separation behind the notch region of a swept tip of a helicopter rotor blade is reduced by features of the geometry and aerodynamic characteristics of the notch region itself. In particular it has been found beneficial for a forwardly swept leading edge portion to extend at an angle between 30 degrees and 55 degrees from a reference line parallel to a blade pitch change axis and the leading edge of the aerofoil in the notch region incorporates blade droop.

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selected citations
These citations are derived from selected sources.
This is an alternative to the "Influence" indicator, which also reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).
BIP!Citations provided by BIP!
popularity
This indicator reflects the "current" impact/attention (the "hype") of an article in the research community at large, based on the underlying citation network.
BIP!Popularity provided by BIP!
influence
This indicator reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).
BIP!Influence provided by BIP!
impulse
This indicator reflects the initial momentum of an article directly after its publication, based on the underlying citation network.
BIP!Impulse provided by BIP!
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Average
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