Wind tunnel test on airfoil Riso-B1-18 with an Active Trailing Edge Flap

Christian Bak, Mac Gaunaa, Peter Bjørn Andersen, Thomas Buhl, Per Hansen, Kasper Clemmensen

    Research output: Contribution to journalJournal articleResearchpeer-review

    Abstract

    A wind tunnel test of the wind turbine airfoil Risø-B1-18 equipped with an Active Trailing Edge Flap (ATEF) was carried out. The ATEF was 9% of the total chord, made of piezo electric actuators attached to the trailing edge of a non-deformable airfoil and actuated using an (electric) amplifier. The airfoil was tested at Re = 1.66 × 106. Steady state and dynamic tests were carried out with prescribed deflections of the ATEF. The steady state tests showed that deflecting the ATEF towards the pressure side (positive ) translated the lift curve to higher lift values and deflecting the ATEF towards the suction side (negative ) translated the lift curve to lower lift values. Testing the airfoil for a step change of the ATEF from = -3.0 to +1.8 showed that the obtainable cl was 0.10 to 0.13 in the linear part of the lift curve. Modeling the step response with an indicial function formulation showed that the time constant in the step change and in sinusoidal deflections in dimensionless terms was T0* = 0.6. Testing the ability of the ATEF to cancel out the load variations for an airfoil in sinusoidal pitch motion of AOA = ±0.7 showed that it was possible to reduce the amplitude with around 80% from cl = 0.148 to cl = 0.032. Copyright © 2009 John Wiley & Sons, Ltd.
    Original languageEnglish
    JournalWind Energy
    Volume13
    Issue number2-3
    Pages (from-to)207-219
    ISSN1095-4244
    DOIs
    Publication statusPublished - 2010

    Keywords

    • Wind energy
    • Aeroelastic design methods

    Cite this

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    title = "Wind tunnel test on airfoil Riso-B1-18 with an Active Trailing Edge Flap",
    abstract = "A wind tunnel test of the wind turbine airfoil Ris{\o}-B1-18 equipped with an Active Trailing Edge Flap (ATEF) was carried out. The ATEF was 9{\%} of the total chord, made of piezo electric actuators attached to the trailing edge of a non-deformable airfoil and actuated using an (electric) amplifier. The airfoil was tested at Re = 1.66 × 106. Steady state and dynamic tests were carried out with prescribed deflections of the ATEF. The steady state tests showed that deflecting the ATEF towards the pressure side (positive ) translated the lift curve to higher lift values and deflecting the ATEF towards the suction side (negative ) translated the lift curve to lower lift values. Testing the airfoil for a step change of the ATEF from = -3.0 to +1.8 showed that the obtainable cl was 0.10 to 0.13 in the linear part of the lift curve. Modeling the step response with an indicial function formulation showed that the time constant in the step change and in sinusoidal deflections in dimensionless terms was T0* = 0.6. Testing the ability of the ATEF to cancel out the load variations for an airfoil in sinusoidal pitch motion of AOA = ±0.7 showed that it was possible to reduce the amplitude with around 80{\%} from cl = 0.148 to cl = 0.032. Copyright {\circledC} 2009 John Wiley & Sons, Ltd.",
    keywords = "Wind energy, Aeroelastic design methods, Aeroelastiske designmetoder, Vindenergi",
    author = "Christian Bak and Mac Gaunaa and Andersen, {Peter Bj{\o}rn} and Thomas Buhl and Per Hansen and Kasper Clemmensen",
    year = "2010",
    doi = "10.1002/we.369",
    language = "English",
    volume = "13",
    pages = "207--219",
    journal = "Wind Energy",
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    publisher = "JohnWiley & Sons Ltd.",
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    }

    Wind tunnel test on airfoil Riso-B1-18 with an Active Trailing Edge Flap. / Bak, Christian; Gaunaa, Mac; Andersen, Peter Bjørn; Buhl, Thomas; Hansen, Per; Clemmensen, Kasper.

    In: Wind Energy, Vol. 13, No. 2-3, 2010, p. 207-219.

    Research output: Contribution to journalJournal articleResearchpeer-review

    TY - JOUR

    T1 - Wind tunnel test on airfoil Riso-B1-18 with an Active Trailing Edge Flap

    AU - Bak, Christian

    AU - Gaunaa, Mac

    AU - Andersen, Peter Bjørn

    AU - Buhl, Thomas

    AU - Hansen, Per

    AU - Clemmensen, Kasper

    PY - 2010

    Y1 - 2010

    N2 - A wind tunnel test of the wind turbine airfoil Risø-B1-18 equipped with an Active Trailing Edge Flap (ATEF) was carried out. The ATEF was 9% of the total chord, made of piezo electric actuators attached to the trailing edge of a non-deformable airfoil and actuated using an (electric) amplifier. The airfoil was tested at Re = 1.66 × 106. Steady state and dynamic tests were carried out with prescribed deflections of the ATEF. The steady state tests showed that deflecting the ATEF towards the pressure side (positive ) translated the lift curve to higher lift values and deflecting the ATEF towards the suction side (negative ) translated the lift curve to lower lift values. Testing the airfoil for a step change of the ATEF from = -3.0 to +1.8 showed that the obtainable cl was 0.10 to 0.13 in the linear part of the lift curve. Modeling the step response with an indicial function formulation showed that the time constant in the step change and in sinusoidal deflections in dimensionless terms was T0* = 0.6. Testing the ability of the ATEF to cancel out the load variations for an airfoil in sinusoidal pitch motion of AOA = ±0.7 showed that it was possible to reduce the amplitude with around 80% from cl = 0.148 to cl = 0.032. Copyright © 2009 John Wiley & Sons, Ltd.

    AB - A wind tunnel test of the wind turbine airfoil Risø-B1-18 equipped with an Active Trailing Edge Flap (ATEF) was carried out. The ATEF was 9% of the total chord, made of piezo electric actuators attached to the trailing edge of a non-deformable airfoil and actuated using an (electric) amplifier. The airfoil was tested at Re = 1.66 × 106. Steady state and dynamic tests were carried out with prescribed deflections of the ATEF. The steady state tests showed that deflecting the ATEF towards the pressure side (positive ) translated the lift curve to higher lift values and deflecting the ATEF towards the suction side (negative ) translated the lift curve to lower lift values. Testing the airfoil for a step change of the ATEF from = -3.0 to +1.8 showed that the obtainable cl was 0.10 to 0.13 in the linear part of the lift curve. Modeling the step response with an indicial function formulation showed that the time constant in the step change and in sinusoidal deflections in dimensionless terms was T0* = 0.6. Testing the ability of the ATEF to cancel out the load variations for an airfoil in sinusoidal pitch motion of AOA = ±0.7 showed that it was possible to reduce the amplitude with around 80% from cl = 0.148 to cl = 0.032. Copyright © 2009 John Wiley & Sons, Ltd.

    KW - Wind energy

    KW - Aeroelastic design methods

    KW - Aeroelastiske designmetoder

    KW - Vindenergi

    U2 - 10.1002/we.369

    DO - 10.1002/we.369

    M3 - Journal article

    VL - 13

    SP - 207

    EP - 219

    JO - Wind Energy

    JF - Wind Energy

    SN - 1095-4244

    IS - 2-3

    ER -