A finite element method for the computation of the transonic flow with shocks past airfoils is presented using the artificial viscosity concept for the local supersonic regime. Generally, the classic element types do not meet the accuracy requirements of advanced numerical aerodynamics requiring special attention to the choice of an appropriate element. A series of computed pressure distributions exhibits the usefulness of the method.


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    Titel :

    A finite element method for the computation of transonic flow past airfoils


    Beteiligte:
    Eberle, A. (Autor:in)

    Erscheinungsdatum :

    01.02.1980


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :




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