A numerical method which simulates the transonic flow around an aircraft and its engines is described. The method solves the transonic potential equations by a finite element technique with automatic mesh generation. The nacelle can be either flow-through or powered with specified inlet conditions. In the latter case the plume is solid. Results for an isolated nacelle and for a complete wing-fuselage-nacelle configuration are shown.


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    Titel :

    Calculation of Transonic Flows around an Aircraft Configuration with Motorized Nacelle


    Beteiligte:
    Y. Vigneron (Autor:in) / T. Lejal (Autor:in)

    Erscheinungsdatum :

    1985


    Format / Umfang :

    11 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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