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Aeroacoustic flowfield and acoustics of a model helicopter tail rotor at high advance ratioSome results, relevant to rotorcraft noise generation process at high advance ratio, are presented in this paper from schlieren flow visualization and acoustic tests of a model tail rotor. The measured in-plane noise trends are consistent with the growth of the tip supersonic region seen in the schlieren visuals. Schlieren flow visuals reveal a propagating pressure wave in the second quadrant. Simultaneously measured acoustic data and the results of two-dimensional transonic Blade-Vortex Interaction analysis code ATRAN-2 indicate that this pressure wave is attributable to BVI activity in the first quadrant. This paper establishes that the transonic Blade-Vortex Interactions contribute to noise at high advance ratio level flight conditions.
Document ID
19900041105
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shenoy, Rajarama K.
(Sikorsky Aircraft Stratford, CT, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Acoustics
Meeting Information
Meeting: AHS Annual Forum
Location: Boston, MA
Country: United States
Start Date: May 22, 1989
End Date: May 24, 1989
Accession Number
90A28160
Funding Number(s)
CONTRACT_GRANT: NAS1-17146
Distribution Limits
Public
Copyright
Other

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