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    Reduction of dynamic stall using a back-flow flap

    Reduction of dynamic stall using a back-flow flap


    Abstract A back-flow flap attached to the suction side of an airfoil is investigated in both passively and actively actuated modes for the control of dynamic stall. This method of dynamic stall control has low power requirements and no parasitic drag when not actuated. Experiments in a low-speed wind tunnel at 50 m/s were used to characterize the reduction in dynamic stall hysteresis using pressure measurements on the midline airfoil section. It was found that the pitching moment peak is reduced by an average of 25% for all deep stall test cases for active actuation of the flap, while for passive actuation the pitching moment peak is reduced by 19%. In each case the maximum lift remained the same, while the peak drag increased by an average of 2.5% for the active flap, and by 0.9% for the passive flap. With the flap closed at low angles of attack, the reference values of the airfoil are retained.

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    Titel :

    Reduction of dynamic stall using a back-flow flap

    Beteiligte:
    Gardner, A. D. (Autor:in) / Opitz, S. (Autor:in) / Wolf, C. C. (Autor:in) / Merz, C. B. (Autor:in)
    Erschienen in:

    CEAS Aeronautical Journal ; 8 , 2

    Erscheinungsdatum :

    2017

    ISSN :

    1869-5582

    DOI :

    https://doi.org/10.1007/s13272-017-0237-4

    Medientyp :

    Aufsatz (Zeitschrift)

    Format :

    Print

    Sprache :

    Englisch

    Schlagwörter :

    Luftfahrttechnik , Raumfahrttechnik

    Klassifikation :

    BKL:    50.03 Methoden und Techniken der Ingenieurwissenschaften / 50.03 Methoden und Techniken der Ingenieurwissenschaften, Methoden und Techniken der Ingenieurwissenschaften / 55.50 Luftfahrzeugtechnik / 55.50 Luftfahrzeugtechnik, Luftfahrzeugtechnik
    DDC:    629.105

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