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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    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


    Contributors:
    D. W. Connor (author) / R. H. Neely (author)

    Publication date :

    1947


    Size :

    50 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English