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Overview of numerical codes developed for predicted electrothermal deicing of aircraft bladesAn overview of the deicing computer codes that have been developed at the University of Toledo under sponsorship of the NASA-Lewis Research Center is presented. These codes simulate the transient heat conduction and phase change occurring in an electrothermal deicier pad that has an arbitrary accreted ice shape on its surface. The codes are one-dimensional rectangular, two-dimensional rectangular, and two-dimensional with a coordinate transformation to model the true blade geometry. All modifications relating to the thermal physics of the deicing problem that have been incorporated into the codes will be discussed. Recent results of reformulating the codes using different numerical methods to increase program efficiency are described. In particular, this reformulation has enabled a more comprehensive two-dimensional code to run in much less CPU time than the original version. The code predictions are compared with experimental data obtained in the NASA-Lewis Icing Research Tunnel with a UH1H blade fitted with a B. F. Goodrich electrothermal deicer pad. Both continuous and cyclic heater firing cases are considered. The major objective in this comparison is to illustrate which codes give acceptable results in different regions of the airfoil for different heater firing sequences.
Document ID
19880034981
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Keith, Theo G.
(Toledo Univ. OH, United States)
De Witt, Kenneth J.
(Toledo Univ. OH, United States)
Wright, William B.
(Toledo Univ. OH, United States)
Masiulaniec, K. Cyril
(Toledo, University OH, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 88-0288
Accession Number
88A22208
Distribution Limits
Public
Copyright
Other

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