An experimental investigation on the transonic flutter characteristics of the cantilever swept-back wing was conducted in a transonic blow-down wind tunnel for flutter testing at Mach numbers from 0.756 to 0.978. The wing models used in the investigation have a swept-back angle of 20 deg at the quater-chord line, panel aspect ratio and taper ratio of 4.0 and 0.4, respectively, utilize the airfoil section of NACA 65A 0012, and include two kinds of configuration of the models, i.e., the clean wing and the wing with a mass of engine-pod shape. The boundaries of flutter-density and experimental flutter-speed coefficients are characterized by the minimum values at certain interim Mach numbers investigated. Also, the results obtained were compared with the previous results of flat-plate wings, and it was found that the wing with airfoil section had a stabilizing effect except in the case of the wing with a mass for high Mach number tested. (Author)


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    Titel :

    An Experimental Investigation on the Transonic Flutter Characteristics of the Cantilever Swept-Back Wing with Airfoil Section and Comparison with the Thin Cantilever Swept-Back Wing


    Beteiligte:
    T. Morita (Autor:in) / E. Nakai (Autor:in) / T. Kikuchi (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    13 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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