A supersonic wind tunnel investigation was conducted in the NASA Langley Unitary Plan Wind Tunnel on an advanced derivative configuration of the United States Air Force F-16 fighter. Longitudinal and lateral directional force and moment data were obtained at Mach numbers of 1.60 to 2.16 to evaluate basic performance parameters and control effectiveness. The aerodynamic characteristics for the F-16 derivative model were compared with the data obtained for the F-16C model and also with a previously tested generic wing model that features an identical plan form shape and similar twist distribution.


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    Title :

    Supersonic Aerodynamic Characteristics of an Advanced F-16 Derivative Aircraft Configuration


    Contributors:
    M. C. Fox (author) / D. K. Forrest (author)

    Publication date :

    1993


    Size :

    122 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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