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:

    Sae Technical Papers


    Contributors:

    Conference:

    Aerospace Technology Conference and Exposition ; 1993



    Publication date :

    1993-09-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Computational Fluid Dynamics with Icing Effects

    Mouch, T. N. / Lan, C. E. / SAE | British Library Conference Proceedings | 1993


    Computational fluid dynamics with icing effects

    Mouch, T.N. / Lan, C.E. | Tema Archive | 1993




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