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Full two-dimensional transient solutions of electrothermal aircraft blade deicingTwo finite difference methods are presented for the analysis of transient, two-dimensional responses of an electrothermal de-icer pad of an aircraft wing or blade with attached variable ice layer thickness. Both models employ a Crank-Nicholson iterative scheme, and use an enthalpy formulation to handle the phase change in the ice layer. The first technique makes use of a 'staircase' approach, fitting the irregular ice boundary with square computational cells. The second technique uses a body fitted coordinate transform, and maps the exact shape of the irregular boundary into a rectangular body, with uniformally square computational cells. The numerical solution takes place in the transformed plane. Initial results accounting for variable ice layer thickness are presented. Details of planned de-icing tests at NASA-Lewis, which will provide empirical verification for the above two methods, are also presented.
Document ID
19850037583
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Masiulaniec, K. C.
(Toledo Univ. OH, United States)
Keith, T. G., Jr.
(Toledo Univ. OH, United States)
Dewitt, K. J.
(Toledo Univ. OH, United States)
Leffel, K. L.
(Toledo, University Toledo, OH, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 85-0413
Accession Number
85A19734
Distribution Limits
Public
Copyright
Other

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