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Measured noise of a scale model high speed propeller at simulated takeoff/approach conditionsA model high-speed advanced propeller, SR-7A, was tested in the NASA Lewis 9x15 foot anechoic wind tunnel at simulated takeoff/approach conditions of 0.2 Mach number. These tests were in support of the full-scale Propfan Text Assessment (PTA) flight program. Acoustic measurements were taken with fixed microphone arrays and with an axially translating microphone probe. Limited aerodynamic measurements were also taken to establish the propeller operating conditions. Tests were conducted with the propeller alone and with three down-stream wing configurations. The propeller was run over a range of blade setting angles from 32.0 deg. to 43.6 deg., tip speeds from 183 to 290 m/sec (600 to 950 ft/sec), and angles of attack from -10 deg. to +15 deg. The propeller alone BPF tone noise was found to increase 10 dB in the flyover plane at 15 deg. propeller axis angle of attack. The installation of the straight wing at minimum spacing of 0.54 wing chord increased the tone noise 5 dB under the wing of 10 deg. propeller axis angle of attack, while a similarly spaced inboard upswept wing only increased the tone noise 2 dB.
Document ID
19870007155
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Woodward, Richard P.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1987
Subject Category
Acoustics
Report/Patent Number
E-3352
NAS 1.15:88920
NASA-TM-88920
AIAA PAPER 87-0526
Accession Number
87N16588
Funding Number(s)
PROJECT: RTOP 535-03-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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