Airfoil performance of a NACA 0012 held at static angles of attack from to 20° in the wake of a circular cylinder is investigated experimentally. Time-averaged airloads were measured for varying cylinder–airfoil streamwise distances, (based on cylinder diameter ), 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 , 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 , 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.
Experimental Investigation of Airfoil Performance in the Wake of a Circular Cylinder
AIAA Journal ; 57 , 7 ; 2808-2818
01.07.2019
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Experimental and Numerical Investigation of Airfoil Performance in Cylinder Wake (AIAA 2018-3232)
British Library Conference Proceedings | 2018
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