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Inflight source noise of an advanced full-scale single-rotation propellerFlight tests to define the far field tone source at cruise conditions were completed on the full scale SR-7L advanced turboprop which was installed on the left wing of a Gulfstream II aircraft. This program, designated Propfan Test Assessment (PTA), involved aeroacoustic testing of the propeller over a range of test conditions. These measurements defined source levels for input into long distance propagation models to predict en route noise. Inflight data were taken for 7 test cases. The sideline directivities measured by the Learjet showed expected maximum levels near 105 degrees from the propeller upstream axis. However, azimuthal directivities based on the maximum observed sideline tone levels showed highest levels below the aircraft. An investigation of the effect of propeller tip speed showed that the tone level of reduction associated with reductions in propeller tip speed is more significant in the horizontal plane than below the aircraft.
Document ID
19910009732
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Woodward, Richard P. (NASA Lewis Research Center Cleveland, OH, United States)
Loeffler, Irvin J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:103687
E-5906
NASA-TM-103687
AIAA PAPER 91-0594
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Reno, NV
Country: United States
Start Date: January 7, 1991
End Date: January 10, 1991
Sponsors: AIAA
Accession Number
91N19045
Funding Number(s)
PROJECT: RTOP 535-03-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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