Airfoil performance of a NACA 0012 held at static angles of attack from 20 ° to 20° in the wake of a circular cylinder is investigated experimentally. Time-averaged airloads were measured for varying cylinder–airfoil streamwise distances, x / D (based on cylinder diameter D ), along with time- and phase-averaged particle image velocimetry. Changes in the cylinder wake flow structure govern airfoil performance in the cylinder–airfoil interaction. For x / D = 2 , the cylinder wake arrangement is a pair of counterrotating vortices in a side-by-side configuration that induce negative drag on the airfoil. As the cylinder–airfoil distance increases to x / D = 3 , the cylinder wake arrangement becomes a von Kármán vortex street that induces an oscillating flow field. A leading edge vortex forms over the NACA 0012 as a consequence of the cylinder wake and delays airfoil stall. This work gives fundamental insight into how large turbulent scales affect airfoil performance in the context of ship–aircraft aerodynamics.


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    Titel :

    Experimental Investigation of Airfoil Performance in the Wake of a Circular Cylinder


    Beteiligte:

    Erschienen in:

    AIAA Journal ; 57 , 7 ; 2808-2818


    Erscheinungsdatum :

    01.07.2019




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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