Predicted electrothermal deicing of aircraft bladesA finite difference method is presented for the transient two-dimensional simulation of an electrothermal de-icer pad of an aircraft wing or blade. The irregular geometry of the composite ice laden blade is handled by use of a body fitted coordinate transformation. By this approach the various blade layers are mapped into a set of stacked rectangular strips in which the numerical solution takes place. Several heat conduction examples are presented in order to demonstrate the accuracy of the numerical procedure. Ice melting time predictions are made and compared to earlier predictions where possible. Finally, a new graphical presentation of thermal results is shown.
Document ID
19840038499
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Keith, T. G., Jr. (Toledo Univ. OH, United States)
Masiulaniec, K. C. (Toledo Univ. OH, United States)
Dewitt, K. J. (Toledo Univ. OH, United States)
Chao, D. F. (Toledo, University Toledo, OH, United States)