Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap


    Contributors:

    Publication date :

    1943-09-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English