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Performance degradation of propeller/rotor systems due to rime ice accretionA theoretical model has been established which is applicable to both propeller and helicopter systems that determines the effect of rime ice accretion on the thrust coefficient, power coefficient, and efficiency as a function of time in a natural icing condition. Theoretical comparisons have been made with experimentally determined decrease in propeller thrust coefficient and efficiency for five natural icing conditions with good agreement. The present analytical model is also applicable to the helicopter case, where the method predicts radial and azimuthal rotor blade ice shapes in addition to torque rise as a function of time in a natural icing condition.
Document ID
19820044787
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Korkan, K. D.
(Texas A & M University College Station, TX, United States)
Dadone, L.
(Boeing Vertol Co. Philadelphia, PA, United States)
Shaw, R. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 82-0286
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Orlando, FL
Start Date: January 11, 1982
End Date: January 14, 1982
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
82A28322
Funding Number(s)
CONTRACT_GRANT: NAG3-109
CONTRACT_GRANT: NAG3-242
Distribution Limits
Public
Copyright
Other

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