The Langley 8-foot transonic pressure tunnel was used at Mach numbers from 0.80 to 1.00 to determine the effects of wing trailing-edge truncation on the aerodynamic characteristics of a 0.0625-scale model of a NASA TF-8A supercritical-wing research airplane. The effects of trailing-edge truncations of 1, 2, and 3 percent of the local streamwise chord on the longitudinal aerodynamic characteristics and the wing section characteristics are presented.


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    Title :

    Effects of Wing Trailing-Edge Truncation on Aerodynamic Characteristics of a NASA Supercritical-Wing Research Airplane Model


    Contributors:

    Publication date :

    1974


    Size :

    106 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English