Wind-tunnel tests were carried out to determine low-speed lift, drag, and pitching moment of the wing tested alone, with various flaps, and in various combinations with the fuselage having 10.2:1 fineness ratio. The results are given in graphs. Rolling-moment characteristics are included in some instances. The locations of aerodynamic centers are given for some configurations and for various wing-fuselage combinations. The table gives characteristics for Reynolds No. 6,840,000 for comparing effects of various flaps. NOTE: Requests for copies of this report must be addressed to: N.A.C.A., Washington, DC.


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    Titel :

    Effects of a Fuselage and Various High-Lift and Stall-Control Flaps on Aerodynamic Characteristics in Ptich of an NACA 64 Series 40 Degree Swept-Back Wing


    Beteiligte:
    D. W. Connor (Autor:in) / R. H. Neely (Autor:in)

    Erscheinungsdatum :

    1947


    Format / Umfang :

    50 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch