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Acoustic measurements of a full-scale coaxial helicopterAcoustic data were obtained during a full-scale test of the XH-59A Advancing Blade Concept (ABC) Technology Demonstrator in the NASA Ames 40- by 80-Foot Wind Tunnel. The XH-59A is a research helicopter with two coaxial rotors and hingeless blades. Performance, vibration, noise at various forward speeds, rotor lift coefficients, and rotor shaft angles of attack were investigated. In general, the noise level is shown to increase with rotor lift coefficient except under certain operating conditions where it is increased by significant impulsive blade/vortex interactions. The impulsivity appears to depend upon how the lift is distributed between the two rotors. The noise levels measured are shown to be slightly higher than on a modern conventional rotor tested in the same facility.
Document ID
19830044715
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mosher, M.
(NASA Ames Research Center Moffett Field, CA, United States)
Peterson, R. L.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 11, 2013
Publication Date
April 1, 1983
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 83-0722
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aeroacoustics Conference
Location: Atlanta, GA
Start Date: April 11, 1983
End Date: April 13, 1983
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
83A25933
Distribution Limits
Public
Copyright
Other

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