We present a medium-fidelity aeroelastic framework for computing intermittently separating three-dimensional (3-D) flows around high-aspect ratio wings with a significantly reduced computational cost compared to the computational-fluid- dynamics-based method. To achieve that, we propose a modified three-dimensional vortex panel method with leading-edge separation controlled by leading-edge suction parameter theory, and its incorporation in a coupled aeroelastic solver for the dynamic response of these systems. Numerical verifications and simulations are presented on both attached and separated aeroelastic test cases, demonstrating the method on postflutter limit-cycle oscillation of a cantilever wing, and leading-edge separation on a deploying wing, a complex kinematic response. In both cases we were able to capture three-dimensional interactions on intermittently separating dynamic flowfields using a low computational cost.


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    Titel :

    Aeroelastic Simulation of High-Aspect Ratio Wings with Intermittent Leading-Edge Separation


    Beteiligte:
    Wang, Yinan (Autor:in) / Zhao, Xiaowei (Autor:in) / Palacios, Rafael (Autor:in) / Otsuka, Keisuke (Autor:in)

    Erschienen in:

    AIAA Journal ; 60 , 3 ; 1769-1782


    Erscheinungsdatum :

    2021-10-13


    Format / Umfang :

    14 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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