This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of the Clark Y airfoil over a large range of Reynolds numbers. Three airfoils of aspect ratio 6 and with 4, 6, and 8 foot chords were tested at velocities between 25 and 118 miles per hour, and the characteristics were obtained for Reynolds numbers (based on the airfoil chord) in the range between 1,000,000 and 9,000,000 at the low angles of attack, and between 1,000,000 and 6,000,000 at maximum lift. With increasing Reynolds number the airfoil characteristics are affected in the following manner: the drag at zero lift decreases, the maximum lift increases, the slope of the lift curve increases, the angle of zero lift occurs at smaller negative angles, and the pitching moment at zero lift does not change appreciably.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Scale Effect on Clark Y Airfoil Characteristics from NACA Full-Scale Wind-Tunnel Tests


    Contributors:

    Publication date :

    1935-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





    The NACA full-scale wind tunnel

    Defrance, Smith J | NTRS | 1934


    Tests of NACA 0025 and 0035 airfoils in full-scale wind tunnel

    Bullivant, W.K. | Engineering Index Backfile | 1941


    Full-Scale Tests of NACA Cowlings

    Theodorsen, Theodore / Brevoort, M J / Stickle, George W | NTRS | 1937