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Computational Simulation of an Electrically Heated Ice Protection System for Composite Leading Edges of Aircraft
Technical Paper
2019-01-2041
ISSN: 0148-7191, e-ISSN: 2688-3627
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English
Abstract
The performance of an electrically heated aircraft ice protection system for a composite leading edge was evaluated. The composite leading edge of the model is equipped with a Ni alloy resistance heater. A state-of-the-art icing code, FENSAP-ICE, was used for the analysis of the electrothermal de-icing system. Computational results, including detailed information of conjugate heat transfer, were validated with experimental data. The computational model was then applied to the composite leading edge wing section at various metrological conditions selected from FAR Part 25 Appendix C.
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Lawrence Raj, P., Jeong, H., Roy, R., Kweon, J. et al., "Computational Simulation of an Electrically Heated Ice Protection System for Composite Leading Edges of Aircraft," SAE Technical Paper 2019-01-2041, 2019, https://doi.org/10.4271/2019-01-2041.Also In
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