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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    Title :

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


    Contributors:
    F. J. Capone (author) / E. A. Bare (author) / D. Arbiter (author)

    Publication date :

    1986


    Size :

    105 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English