Numerical simulation of electrothermal de-icing systemsTransient simulations of de-icing of composite aircraft components by electrothermal heating have been computed for both one and two-dimensional rectangular geometries. The implicit Crank-Nicolson formulation is used to insure stability of the finite-differenced heat conduction equations and the phase change in the ice layer is simulated using the Enthalpy method. Numerical solutions illustrating de-icer performance for various composite aircraft blades and environmental conditions are presented. Comparisons are made with previous studies and with available experimental data. Initial results using a coordinate mapping technique to describe the actual blade geometry are discussed.
Document ID
19830054825
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
De Witt, K. J. (Toledo Univ. OH, United States)
Keith, T. G. (Toledo Univ. OH, United States)
Chao, D. F. (Toledo Univ. OH, United States)
Masiulaniec, K. C. (Toledo, University Toledo, OH, United States)