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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    Title :

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


    Contributors:

    Published in:

    AIAA Journal ; 57 , 7 ; 2808-2818


    Publication date :

    2019-07-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



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