This paper presents an experimental investigation of the control of airfoil aerodynamics at a low Reynolds number of 5 × 10 4 within a wide range of attack angle α using a leading-edge-protuberance technique. The essence of the technique is to manipulate flow around the airfoil by replacing the straight leading edge of a baseline airfoil with a sinusoidal wavy airfoil. Whereas the lift and drag forces and the lift-to-drag ratio were measured using a three-component force balance, the flow was mainly measured using a particle-image velocimetry. The sinusoidal protuberances effectively suppressed airfoil stall, and the corresponding aerodynamic performance was impaired to some extent. Meanwhile, control significantly improved the airfoil aerodynamics in the poststall α region, for example, 16 < α < 70 deg , leading to a maximum 25.0 and 39.2% increase in lift coefficient and lift-to-drag ratio, respectively, and a maximum 20.0% decrease in drag coefficient. The protuberances may influence control performance in a similar way with low-profile vortex generators. The flow physics behind the observations were discussed in detail.


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    Titel :

    Aerodynamic Control of Low-Reynolds-Number Airfoil with Leading-Edge Protuberances


    Beteiligte:
    Zhang, M. M. (Autor:in) / Wang, G. F. (Autor:in) / Xu, J. Z. (Autor:in)

    Erschienen in:

    AIAA Journal ; 51 , 8 ; 1960-1971


    Erscheinungsdatum :

    2013-05-17


    Format / Umfang :

    12 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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