An investigation was conducted in the Langley 8 foot transonic pressure tunnel to determine the effects of wing transition location and of slotted and unslotted full span flaps on the longitudinal aerodynamic characteristics of a 1/15 scale model of a variable wing sweep tactical fighter model. Tests were at Mach numbers from 0.70 to 0.85 for a wing leading edge sweep of 26 deg.


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    Title :

    Effect of Wing-Transition Location and Slotted and Unslotted Flaps on Aerodynamic Characteristics of a Fighter Model at High Subsonic Speeds


    Contributors:
    T. G. Ayers (author)

    Publication date :

    1969


    Size :

    46 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English