A program for the wind tunnel development of underwing leading-edge vortex generators on an NASA supercritical-wing research airplane model was conducted in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.25 to 0.99. The effects on the longitudinal aerodynamic characteristics of vortex-generator wing semispan location, distance from wing leading edge, leading-edge sweep angle, toe-in angle, and span are presented. The effects of the vortex generators on the lateral-directional aerodynamic characteristics of the model for a sideslip angle of 5 deg are included.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wind-tunnel development of underwing leading-edge vortex generators on a NASA supercritical-wing research airplane configuration


    Contributors:

    Publication date :

    1973-11-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English