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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    Titel :

    Effects of wing trailing-edge truncation on aerodynamic characteristics of a NASA supercritical-wing research airplane model


    Beteiligte:
    Bartlett, D. W. (Autor:in) / Harris, C. D. (Autor:in)

    Erscheinungsdatum :

    1974-08-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :