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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

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


    Beteiligte:
    M. C. Fox (Autor:in) / D. K. Forrest (Autor:in)

    Erscheinungsdatum :

    1993


    Format / Umfang :

    122 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Research progress of aerodynamic configuration technology of low sonic boom supersonic aircraft

    SU Fengnian / ZHONG Ping / ZENG Hui et al. | DOAJ | 2023

    Freier Zugriff

    Aerodynamic investigation of supersonic aircraft configurations

    Paparone, L. / Confederation of European Aerospace Societies | British Library Conference Proceedings | 1995


    Aerodynamic design integration of supersonic aircraft

    Baals, D. D. / Harris, R. V., Jr. / Robins, A. W. | NTRS | 1970


    Aerodynamic Design Integration of Supersonic Aircraft

    DONALD D. BAALS / A. WARNER ROBINS / AND ROY V. HARRIS | AIAA | 1970