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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    Title :

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


    Contributors:
    Eberle, A. (author)

    Publication date :

    1980-02-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :




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