This study describes the development of an integrated aerothermoelastic computational framework. The framework consists of a Navier–Stokes aerodynamic solver based on an Automatic Differentiation flow solver code; a finite element structural solver for moderate deflection of a composite, doubly curved, shallow shell with thermal stress; and a finite element thermal solver for heat transfer in composite shallow shells with nonlinear material properties. The solvers are loosely coupled using a partitioned scheme. An analytical approach is developed to determine the time accuracy and the so-called energy accuracy of a loosely coupled scheme, which serves as a guide for designing schemes having a high convergence rate. The aeroelastic and aerothermoelastic behaviors of two-dimensional and three-dimensional panels are investigated using the computational framework. The effects of the aspect ratio and boundary-layer thickness are found to have significant influence on the critical flutter parameter and the onset time of aerothermoelastic instability.


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    Titel :

    Integrated Aerothermoelastic Analysis Framework with Application to Skin Panels


    Beteiligte:
    Huang, Daning (Autor:in) / Rokita, Tomer (Autor:in) / Friedmann, Peretz P. (Autor:in)

    Erschienen in:

    AIAA Journal ; 56 , 11 ; 4562-4581


    Erscheinungsdatum :

    2018-09-20


    Format / Umfang :

    20 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch