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Effect of at-the-source noise reduction on performance and weights of a tilt-rotor aircraftReduction of far-field acoustic signature through modification of basic design parameters (tip speed, number of blades, disc loading and rotor blade area) was examined, using a tilt-rotor flight research aircraft as a baseline configuration. Of those design parameters, tip speed appeared as the most important. Next, preliminary design of two aircraft was performed, postulating the following reduction of noise level from that of the baseline machine, at 500 feet from the spot of OGE hover. In one aircraft, the PNL was lowered by 10 PNdB and in the other, OASPL decreased by 10 dB. The resulting weight and performance penalties were examined. Then, PNL and EPNL aspects of terminal operation were compared for the baseline and quieter aircraft.
Document ID
19750034312
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gibs, J.
Stepniewski, W. Z.
Spencer, R.
(Boeing Vertol Co. Philadelphia, Pa., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1975
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 75-205
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: Pasadena, CA
Start Date: January 20, 1975
End Date: January 22, 1975
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
75A18384
Funding Number(s)
CONTRACT_GRANT: NAS2-6784
Distribution Limits
Public
Copyright
Other

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