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A numerical and experimental investigation of electrothermal aircraft deicingExperimental data were obtained for the deicing characteristics of a stationary UH-1H helicopter blade which had been fitted with an electrothermal deicer assembly. The tests were run in the NASA Lewis Icing Research Tunnel, and yielded transient temperature responses for the substrate, heater and abrasion shield at selected positions around the blade. The data at the abrasion shield-ice interface clearly documented when melting, shedding or refreezing occurred. Comparisons were made between the experimental data and a one-dimensional numerical model. The agreement was generally very good, with the simulations being shown to be capable of predicting the transient temperature responses along with phase change and ice shedding. At many blade positions, the model was capable of accurately simulating the thermal response of the electrothermal deicer assembly.
Document ID
19870031997
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Leffel, K.
(Toledo Univ. OH, United States)
Masiulaniec, K. C.
(Toledo Univ. OH, United States)
Dewitt, K. J.
(Toledo Univ. OH, United States)
Keith, T. G., Jr.
(Toledo, University OH, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1986
Subject Category
Aircraft Design, Testing And Performance
Accession Number
87A19271
Distribution Limits
Public
Copyright
Other

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