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Computational Simulation of an Electrically Heated Ice Protection System for Composite Leading Edges of Aircraft
ISSN: 0148-7191, e-ISSN: 2688-3627
Published June 10, 2019 by SAE International in United States
Annotation ability available
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.
CitationLawrence 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.
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