A simplified, uncoupled zonal procedure was utilized to assess the capability of numerically simulating icing effects on a Boeing 727-200 aircraft. The computational approach combines potential flow, plus boundary layer simulations by VSAERO for the un-iced aircraft forces and moments, with Navier-Stokes simulations by ARC3D for the incremental forces and moments due to iced components. These are compared with wind tunnel longitudinal force and moment data. Although the computational results compared favorably with the test data in the linear angle of attack range, it is clear that for general aircraft icing calculations, a multiblock Navier-Stokes code will be required for the viscous component of this zonal method.


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    Title :

    CFD zonal modeling of leading-edge ice effects for a complete aircraft


    Contributors:

    Conference:

    AIAA, Aerospace Sciences Meeting and Exhibit ; 1993 ; Reno, NV, United States


    Publication date :

    1993-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    CFD zonal modeling of leading-edge ice effects for a complete aircraft

    SUMMA, J. / STRASH, D. / LEDNICER, D. | AIAA | 1993


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    Improved CFD Zonal Modeling of Leading-Edge Ice Effects for a Complete Aircraft

    Strash, D. J. / Summa, J. M. / AIAA | British Library Conference Proceedings | 1994


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