Some experimental flutter results are presented over a Mach number range from about 0.70 to 0.95 for a simple, swept, tapered, flat-plate wing model having a planform representative of subsonic transport airplanes and for the same wing model equipped with two different upper surface winglets. Both winglets had the same planform and area (about 2 percent of the basic-wing area); however, one weighed about 0.3 percent of the basic-wing weight, and the other weighed about 1.8 percent of the wing weight. The addition of the lighter winglet reduced the wing-flutter dynamic pressure by about 3 percent; the heavier winglet reduced the wing-flutter dynamic pressure by about 12 percent. The experimental flutter results are compared at a Mach number of 0.80 with analytical flutter results obtained by using doublet-lattice and lifting-surface (kernel-function) unsteady aerodynamic theories.


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    Titel :

    Preliminary study of effects of winglets on wing flutter


    Beteiligte:

    Erscheinungsdatum :

    01.12.1976


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Preliminary Study of Effects of Winglets on Wing Flutter

    R. V. Doggett / M. G. Farmer | NTIS | 1976


    Preliminary study of effects of winglets on wing flutter

    Doggett, Robert V. / Farmer, Moses G. | TIBKAT | 1976


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