A computational method which simulates transonic flow about wing-fuselage configurations has been extended to include the treatment of multiple body and non-planar wing surfaces. The finite difference relaxation scheme is characterized by a modified small disturbance flow equation and multiple embedded grid system. Wing-body combinations with as many as four nacelles/pods, four pylons, and wing-tip-mounted winglets can be analyzed. A scheme for modeling inlet spillage and engine exhaust interference effects has been included. Computed results are correlated with experimental data for three transport configurations.


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    Title :

    Simulated transonic flows for aircraft with nacelles, pylons, and winglets


    Contributors:
    Boppe, C. W. (author) / Stern, M. A. (author)

    Conference:

    Aerospace Sciences Meeting ; 1980 ; Pasadena, CA


    Publication date :

    1980-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :