Wind Tunnel Testing of an S809 Spoiler Flap Model

    Research output: Contribution to conferencePaper


    An 18-inch chord model of the NREL S809 airfoil section with a spoiler flap was tested under two dimensional steady state conditions in The Ohio State University Aeronautical and Astronautical Research Laboratory 7x10 Subsonic Wind Tunnel. The objective of these tests was to document section lift, drag and pitching moment characteristics over a wide range of flap deflections and angles of attack.The model was tested under both clean and leading edge grit roughness (LEGR) conditions. The LEGR was used to simulate the accumulation of insects and debris on the leading edge of the rotor blades found in the field. The configuration exhibited a clean maximum lift coefficient of 1.12. The application of LEGR reduced the maximum lift coefficient and increased the drag for low angles of attackand low flap deflections. The LEGR was found to have negligible effect at high angles of attack (above 20 degrees) and high aileron deflection (above 45 degrees). At high aileron deflections (greater than 30 degrees), the suction coefficient was negative in the region of -6 degrees to 30 degrees angle of attack. Over the 276 degree angle of attack range, the hinge moment coefficients varied from-0.16 to 0.15 for the spoiler flap.
    Original languageAmerican English
    Number of pages10
    StatePublished - 1997
    Event1997 ASME Wind Energy Symposium Technical 35th AIAA Aerospace Sciences Meeting and Exhibit - Reno, Nevada
    Duration: 6 Jan 19979 Jan 1997


    Conference1997 ASME Wind Energy Symposium Technical 35th AIAA Aerospace Sciences Meeting and Exhibit
    CityReno, Nevada

    Bibliographical note

    Work performed by Ohio State University, Columbus, Ohio

    NREL Publication Number

    • NREL/CP-23294


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