A model of the Grumman/Navy F-14A aircraft was developed for analyses using the NASA/Grumman Transonic Wing-Body Code. Computations were performed for isolated wing and wing fuselage glove arrangements to determine the extent of aerodynamic interference effects which propagate outward onto the main wing outer panel. Additional studies were conducted using the full potential analysis, FLO 22, to calibrate any inaccuracies that might accrue because of small disturbance code limitations. Comparisons indicate that the NASA/Grumman code provides excellent flow simulations for the range of wing sweep angles and flow conditions that will be of interest for the upcoming F-14 Variable Sweep Flight Transition Experiment.


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    Title :

    F-14A Aircraft High-Speed Flow Simulations


    Contributors:
    C. W. Boppe (author) / B. S. Rosen (author)

    Publication date :

    1985


    Size :

    204 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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