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Acoustic Shielding for a Model Scale Counter-rotation Open RotorThe noise shielding benefit of installing an open rotor above a simplified wing or tail is explored experimentally. The test results provide both a benchmark data set for validating shielding prediction tools and an opportunity for a system level evaluation of the noise reduction potential of propulsion noise shielding by an airframe component. A short barrier near the open rotor was found to provide up to 8.5 dB of attenuation at some directivity angles, with tonal sound particularly well shielded. Predictions from two simple shielding theories were found to overestimate the shielding benefit.
Document ID
20120002629
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
David B Stephens (Glenn Research Center Cleveland, Ohio, United States)
Edmane Envia (Glenn Research Center Cleveland, Ohio, United States)
Date Acquired
August 25, 2013
Publication Date
January 1, 2012
Publication Information
Publication: 17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)
e-ISBN: 9781600869433
DOI: 10.2514/6.2011-2940
Subject Category
Acoustics
Report/Patent Number
NASA/TM-2012-217227
E-17910
AIAA-2011-2940
Meeting Information
Meeting: 17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)
Location: Portland, OR
Country: US
Start Date: June 5, 2011
End Date: June 8, 2011
Sponsors: Council of European Aerospace Societies, American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 561581.02.08.03.18.16
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
NASA Peer Committee
Keywords
Acoustics shielding
Open rotor
Airframes
Sound pressure level
Low speed wind tunnel
Propeller noise
Shear layers
NASA Glenn Research Center
Aircraft propulsion
Rotor blades
Aerodynamic design
Blended wing body

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