The aerodynamic characteristics of an advanced twin-engine fighter aircraft designed for supersonic cruise have been studied in the Langley 16-Foot Transonic Tunnel and the Lewis 10- by 10-Foot Supersonic Tunnel. The objective of this investigation was to establish an aerodynamic data base for the configuration with flow-through nacelles and representative inlets. The use of a canard for trim and the effects of fairing over the inlets were assessed. Comparisons between experimental and theoretical results were also made. The theoretical results were determined by using a potential vortex lift code for subsonic speeds and a linear aerodynamic code for supersonic speeds. This investigation was conducted at Mach numbers from 0.40 to 2.47, at angles of attack from 0 deg to about 20 deg, and at inlet capture ratios of about 0.5 to 1.4.


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    Titel :

    Aerodynamic Characteristics of a Supersonic Fighter Aircraft Model at Mach 0.40 to 2.47


    Beteiligte:
    F. J. Capone (Autor:in) / E. A. Bare (Autor:in) / D. Arbiter (Autor:in)

    Erscheinungsdatum :

    1986


    Format / Umfang :

    105 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch