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Results of a sub-scale model rotor icing testA heavily instrumented sub-scale model of a helicopter main rotor was tested in the NASA Lewis Research Center Icing Research Tunnel (IRT) in September and November 1989. The four-bladed main rotor had a diameter of 1.83 m (6.00 ft) and the 0.124 m (4.9 in) chord rotor blades were specially fabricated for this experiment. The instrumented rotor was mounted on a Sikorsky Aircraft Powered Force Model, which enclosed a rotor balance and other measurement systems. The model rotor was exposed to a range of icing conditions that included variations in temperature, liquid water content, and median droplet diameter, and was operated over ranges of advance ratio, shaft angle, tip Mach number (rotor speed) and weight coefficient to determine the effect of these parameters on ice accretion. In addition to strain gage and balance data, the test was documented with still, video, and high speed photography, ice profile tracings, and ice molds. The sensitivity of the model rotor to the test parameters is given, and the result to theoretical predictions are compared. Test data quality was excellent, and ice accretion prediction methods and rotor performance prediction methods (using published icing lift and drag relationships) reproduced the performance trends observed in the test. Adjustments to the correlation coefficients to improve the level of correlation are suggested.
Document ID
19910041567
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Flemming, Robert J.
(Sikorsky Aircraft Stratford, CT, United States)
Bond, Thomas H.
(NASA Lewis Research Center Cleveland, OH, United States)
Britton, Randall K.
(NASA Lewis Research Center; Sverdrup Technology, Inc. Cleveland, OH, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Air Transportation And Safety
Report/Patent Number
AIAA PAPER 91-0660
Accession Number
91A26190
Distribution Limits
Public
Copyright
Other

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