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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    Title :

    Computational Simulation of an Electrically Heated Ice Protection System for Composite Leading Edges of Aircraft


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    International Conference on Icing of Aircraft, Engines, and Structures ; 2019



    Publication date :

    2019-06-10




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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