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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    Titel :

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


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Jeong, Hojin (Autor:in) / Kweon, Jin-Hwe (Autor:in) / Lawrence Raj, Prince Raj (Autor:in) / Roy, Rene (Autor:in) / Myong, Rho Shin (Autor:in)

    Kongress:

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



    Erscheinungsdatum :

    10.06.2019




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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

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    Electro-thermal Ice Protection for Leading Edges on Large Aircraft

    Nielsen, T. / Royal Aeronautical Society | British Library Conference Proceedings | 2004


    Smart Thermal Protection Leading Edges

    Keller, K. / Lampani, L. / Ritter, H. et al. | British Library Conference Proceedings | 2006


    Flow-thermal-structural study of aerodynamically heated leading edges

    DECHAUMPHAI, PRAMOTE / WIETING, ALLAN R. / THORNTON, EARL A. | AIAA | 1989


    Flow-thermal-structural study of aerodynamically heated leading edges

    Dechaumphai, Pramote / Wieting, Allan R. / Thornton, Earl A. | NTRS | 1989