Experiences at the NASA Langley Research Center generating grids about a cranked wing fighter aircraft configuration is described. A single block planar grid about the fuselage and canard used with a finite difference Navier-Stokes solver is also described. A dual block nonplanar grid about the complete configuration and used with a finite volume Euler solver is presented. The very important aspect of computing the aircraft surface grid, starting with a standardized model description, is also presented.


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    Title :

    Grid generation on and about a cranked-wing fighter aircraft configuration


    Contributors:


    Publication date :

    1988-03-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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