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Icing tunnel tests of Electro-Impulse De-Icing of an engine inlet and high-speed wingsA brief review is given of four earlier tests in the NASA Lewis Icing Research Tunnel and of flight tests in NASA's Icing Research Aircraft and in a Cessna 206 airplane. Details are given of recent icing tunnel tests of thicker-skinned wings, a Gates Learjet, a composite leading edge, and a Boeing 767, and of a Falcon Fanjet engine inlet. These were tested at speeds from 87 to 220 knots, air temperatures from -2 to -15 C, LWC values of 0.6 to 2.4 grams/cu meter, and median droplet diameters from 12 to 20 microns. Energy requirements are reported, as well as conclusions from comparisons of several Electro-Impulse De-Icing coil system designs. Fundamental studies of the structural dynamics and ice shedding of a 12.7 cm (5 inch) diameter semicylinder are described. Some potential problem areas are discussed: fatigue of skin and coil mountings, system weight and cost, electro-magnetic interference and noise.
Document ID
19850038721
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Zumwalt, G. W.
(Wichita State University Wichita, KS, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
Air Transportation And Safety
Report/Patent Number
AIAA PAPER 85-0466
Accession Number
85A20872
Funding Number(s)
CONTRACT_GRANT: NAG3-284
Distribution Limits
Public
Copyright
Other

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