NASA NTRS · 19830054825
Numerical simulation of electrothermal de-icing systems
Abstract
Transient 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.
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De Witt, K. J., Keith, T. G., Chao, D. F., Masiulaniec, K. C.. 1983-01-01. Numerical simulation of electrothermal de-icing systems. https://ntrs.nasa.gov/citations/19830054825
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