A quick, computationally inexpensive technique has been developed for the analysis of a full aircraft configuration with iced surfaces. Viscous effects for the flow field about an airfoil with an iced leading edge are accounted for in a thin-layer Navier Stokes code (ARC2D). A panel code (PMARC) solves the flow field away from the body. The results of the airfoil analysis represent the near-field solutions and are used to modify the boundary conditions in the three-dimensional calculations with the panel code by matching the local circulation. This process is repeated until the total lift coefficient between successive iterations differs by less than a specified value. Examples showing good comparison between the 3-D calculations and experimental data are provided.


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    Title :

    Computational fluid dynamics with icing effects


    Additional title:

    Rechnerische Dynamik von flüssigen Körpern in Bezug auf Vereisung im Luftfahrtbereich


    Contributors:
    Mouch, T.N. (author) / Lan, C.E. (author)

    Published in:

    Publication date :

    1993


    Size :

    12 Seiten, 18 Bilder, 23 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Computational Fluid Dynamics with Icing Effects

    Lan, C. Edward / Mouch, Thomas N. | SAE Technical Papers | 1993



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