The influence of upper-surface nacelle exhaust flow on the aerodynamic characteristics of a supersonic cruise aircraft research configuration was investigated in a 16 foot transonic tunnel over a range of Mach numbers from 0.60 to 1.20. The arrow-wing transport configuration with engines suspended over the wing was tested at angles of attack from -4 deg to 6 deg and jet total pressure ratios from 1 to approximately 13. Wing-tip leading edge flap deflections of -10 deg to 10 deg were tested with the wing-body configuration. Various nacelle locations (chordwise, spanwise, and vertical) were tested over the ranges of Mach numbers, angles of attack, and jet total-pressure ratios. The results show that reflecting the wing-tip leading edge flap from 0 deg to -10 deg increased the maximum lift-drag ratio by 1.0 at subsonic speeds. Jet exhaust interference effects were negligible.


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    Title :

    Transonic Aerodynamic Characteristics of a Supersonic Cruise Aircraft Research Model with the Engines Suspended Above the Wing


    Contributors:
    C. E. Mercer (author) / G. T. Carson (author)

    Publication date :

    1979


    Size :

    198 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English