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Summary of recent NASA propeller researchAdvanced high-speed propellers offer large performance improvements for aircraft that cruise in the Mach 0.7 to 0.8 speed regime. At these speeds, studies indicate that there is a 15 to near 40 percent block fuel savings and associated operating cost benefits for advanced turboprops compared to equivalent technology turbofan powered aircraft. Recent wind tunnel results for five eight to ten blade advanced models are compared with analytical predictions. Test results show that blade sweep was important in achieving net efficiencies near 80 percent at Mach 0.8 and reducing nearfield cruise noise by about 6 dB. Lifting line and lifting surface aerodynamic analysis codes are under development and some results are compared with propeller force and probe data. Also, analytical predictions are compared with some initial laser velocimeter measurements of the flow field velocities of an eightbladed 45 swept propeller. Experimental aeroelastic results indicate that cascade effects and blade sweep strongly affect propeller aeroelastic characteristics. Comparisons of propeller near-field noise data with linear acoustic theory indicate that the theory adequately predicts near-field noise for subsonic tip speeds but overpredicts the noise for supersonic tip speeds.
Document ID
19840024274
Document Type
Conference Paper
Authors
Mikkelson, D. C. (NASA Lewis Research Center Cleveland, OH, United States)
Mitchell, G. A. (NASA Lewis Research Center Cleveland, OH, United States)
Bober, L. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1984
Subject Category
AERONAUTICS (GENERAL)
Report/Patent Number
E-2216
NAS 1.15:83733
NASA-TM-83733
Meeting Information
AGARD Fluid Dyn. Panel Meeting on Aerodyn. and Acoustics of Propellers(Toronto)
Funding Number(s)
PROJECT: RTOP 505-40-32
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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