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Full-Scale Tests of 4- and 6-Blade, Single- and Dual-Rotating Propellers, Special ReportTest of 10-foot diameter, 4- and 6-blade single- and dual-rotating propellers were conducted in the 20-foot propeller-research tunnel. The propellers were mounted at the front end of a streamline body incorporating spinners to house the hub portions. The effect of a symmetrical wing mounted in the slipstream was investigated. The blade angles investigated ranged from 20 degrees to 65 degrees; the latter setting corresponds to airplane speeds of over 500 miles per hour. The results indicate that dual-rotating propellers were from 0 to 6% more efficient than single-rotating ones; but when operating in the presence of a wing the gain was reduced about one-half. Other advantages of dual-rotating propellers were found to include greater power absorption and greater efficiency at the low V/nD operating range of high pitch propellers.
Document ID
20090014884
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Biermann, David (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Hartman, Edwin P. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 1940
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-SR-157
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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