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Preliminary Results of Cyclical De-Icing of a Gas-Heated AirfoilAn NACA 65(sub 1)-212 airfoil of 8-foot chord was provided with a gas-heated leading edge for investigations of cyclical de-icing. De-icing was accomplished with intermittent heating of airfoil segments that supplied hot gas to chordwise passages in a double-skin construction. Ice removal was facilitated by a spanwise leading-edge parting strip which was continuously heated from the gas-supply duct. Preliminary results demonstrate that satisfactory cyclical ice removal occurs with ratios of cycle time to heat-on period (cycle ratio) from 10 to 26. For minimum runback, efficient ice removal, and minimum total heat input, short heat-on periods of about 15 seconds with heat-off periods of 260 seconds gave the best results. In the range of conditions investigated, the prime variables in the determination of the required heat input for cyclical ice removal were the air temperature and the cycle ratio; heat-off period, liquid water content, airspeed, and angle of attack had only secondary effects on heat input rate.
Document ID
19810068710
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Gray, V. H.
(National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Bowden, D. T.
(National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
VonGlahn, U.
(National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
January 24, 1952
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NACA-RM-E51J29
Accession Number
81N73132
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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