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Wind-Tunnel Results of Advanced High-Speed Propellers at Takeoff, Climb, and Landing Mach NumbersLow-speed wind-tunnel performance tests of two advanced propellers have been completed at the NASA Lewis Research Center as part of the NASA Advanced Turboprop Program. The 62.2 cm (24.5 in.) diameter adjustable-pitch models were tested at Mach numbers typical of takeoff, initial climbout, and landing speeds (i.e., from Mach 0.10 to 0.34) at zero angle of attack in the NASA Lewis 10 by 10 Foot Supersonic Wind Tunnel. Both models had eight blades and a cruise-design-point operating condition of Mach 0.80, and 10.668 km (35,000 ft) I.S.A. altitude, a 243.8 m/s (800 ft/sec) tip speed, and a high power loading of 301 kW/sq m (37.5 shp/sq ft). Each model had its own integrally designed area-ruled spinner, but used the same specially contoured nacelle. These features reduced blade-section Mach numbers and relieved blade-root choking at the cruise condition. No adverse or unusual low-speed operating conditions were found during the test with either the straight blade SR-2 or the 45 deg swept SR-3 propeller. Typical efficiencies of the straight and 45 deg swept propellers were 50.2 and 54.9 percent, respectively, at a takeoff condition of Mach 0.20 and 53.7 and 59.1 percent, respectively, at a climb condition of Mach 0.34.
Document ID
19890009894
Document Type
Technical Memorandum (TM)
Authors
Stefko, George L.
(NASA Lewis Research Center Cleveland, OH, United States)
Jeracki, Robert J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
November 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-87030
E-2417
NAS 1.15:87030
Accession Number
89N19265
Funding Number(s)
PROJECT: RTOP 505-45-48
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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