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NASA Advanced Propeller ResearchAcoustic and aerodynamic research at NASA Lewis Research Center on advanced propellers is reviewed including analytical and experimental results on both single and counterrotation. Computational tools used to calculate the detailed flow and acoustic i e l d s a r e described along with wind tunnel tests to obtain data for code verification . Results from two kinds of experiments are reviewed: ( 1 ) performance and near field noise at cruise conditions as measured in the NASA Lewis 8-by 6-Foot Wind Tunnel and ( 2 ) farfield noise and performance for takeoff/approach conditions as measured in the NASA Lewis 9-by 15-Font Anechoic Wind Tunnel. Detailed measurements of steady blade surface pressures are described along with vortex flow phenomena at off design conditions . Near field noise at cruise is shown to level out or decrease as tip relative Mach number is increased beyond 1.15. Counterrotation interaction noise is shown to be a dominant source at take off but a secondary source at cruise. Effects of unequal rotor diameters and rotor-to-rotor spacing on interaction noise a real so illustrated. Comparisons of wind tunnel acoustic measurements to flight results are made. Finally, some future directions in advanced propeller research such as swirl recovery vanes, higher sweep, forward sweep, and ducted propellers are discussed.
Document ID
20040084639
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Groeneweg, John F. (NASA Lewis Research Center Cleveland, OH, United States)
Bober, Lawrence J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 21, 2013
Publication Date
January 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
E-4393
NASA-TM-101361
Meeting Information
Meeting: Advanced Propellers and Their Installation on Aircraft
Location: Cranfield
Country: United Kingdom
Start Date: September 26, 1988
End Date: September 27, 1988
Sponsors: Royal Aeronautical Society
Funding Number(s)
OTHER: 22-781-30-50
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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