Results from the initial wind-tunnel test of a large-scale, highly maneuverable supersonic V/STOL fighter model in the Ames 40- by 80-foot wind tunnel are summarized. The STOL configuration which was tested combined upper surface blowing and spanwise blowing to improve the lift characteristics over a wide angle-of-attack range. A close-coupled canard was added to this configuration to create a highly maneuverable STOL aircraft. The 7.28 m (24 ft) span model was powered by two J-97 turbojet engines, each producing 9340 N (2200 lb) thrust at a pressure ratio of 2. With the nozzle flap and aileron set at 30 deg, the model produced lift coefficients greater than 4. The model was longitudinally unstable because of the forward canard position and because of the large body area of fuselage, strake, and nacelles forward of the center of gravity.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wind-Tunnel Investigation of Highly Maneuverable Supersonic V/STOL Fighter


    Contributors:
    M. Falarski (author)

    Publication date :

    1979


    Size :

    24 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English