An exploratory program was conducted under the sponsorship of the USAF AFWAL Aero Propulsion Laboratory to investigate a range of exhaust system concepts with the potential to significantly improve the short field capability of advanced tactical aircraft. As a result of these studies, an advanced STOL combat vehicle has been configured which can achieve field lengths of less than 1000 feet with minimal impact on other aircraft performance parameters. This is done using the vectored bypass flow from an unmixed turbofan engine to provide propulsive lift during the approach and landing phase. The bypass flow from the engine exhausts through two vectoring nozzles located on either side of the fuselage close to the center of gravity. This location minimizes the impact of thrust vectoring on the aircraft pitch characteristics. The air vehicle was configured and sized to achieve a 700 foot field length with landing being the critical mission element. Two echaust nozzle concepts were selected for detailed study in the context of this aircraft and a series of experimental evaluation carried out to determine the internal and installed performance of these nozzles over the transonic regime. Vehicle characteristics and nozzle flowfield during approach andlanding were evaluated in a low speed wind tunnnel test. Development of the propulsion system and exhaust nozzle concepts and their integration into the air vehicle are presented together with the aircraft characteristics determined during the experimental phase.


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    Titel :

    STOL characteristics of a tactical aircraft with thrust vectoring nozzles


    Weitere Titelangaben:

    Senkrechtstarteigenschaften eines taktischen Militaerflugzeugs mit Schubumkehrduesen


    Beteiligte:
    Tape, R.F. (Autor:in) / Glidewell, R.J. (Autor:in) / Berndt, D.E. (Autor:in)

    Erschienen in:

    AIAA-Papers ; Jul ; 1-9


    Erscheinungsdatum :

    1987


    Format / Umfang :

    9 Seiten, 19 Bilder, 3 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    STOL characteristics of a tactical aircraft with thrust vectoring nozzles

    TAPE, ROBERT / GLIDEWELL, RONALD / BERNDT, DAVID | AIAA | 1987


    Integration of vectoring nozzles in a STOL transonic tactical aircraft

    BERNDT, D. / GLIDEWELL, R. / BARNES, G. | AIAA | 1985


    Aircraft thrust vectoring using flexible nonaxisymmetric nozzles

    Whitaker, Kevin W. / Gowadia, Noshir S. | AIAA | 1994