Computational Simulation of an Electrically Heated Ice Protection System for Composite Leading Edges of Aircraft 2019-01-2041
An investigation was conducted to evaluate the performance of an electrically heated aircraft ice protection system for the composite leading edge. The composite leading edge of the model is equipped with a polymide film heater. In this computational study, a state-of-the-art icing code, FENSAP-ICE, is used for the analysis of the electrothermal de-icing system. Computational results including detailed conjugate heat transfer analysis are then validated with experimental data and the same computational model is applied to the composite leading edge wing section.
Prince Raj Lawrence Raj, Hojin Jeong, Rene Roy, Jin-Hwe Kweon, Rho Shin Myong
Gyeongsang National University
International Conference on Icing of Aircraft, Engines, and Structures