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

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 phas...

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Bibliographic Details
Published in:AIAA journal 2019-07, Vol.57 (7), p.2808-2818
Main Authors: Lefebvre, Jonathan N, Jones, Anya R
Format: Article
Language:English
Subjects:
Aerodynamics
Angle of attack
Circular cylinders
Diameters
Flow control
Fluid dynamics
Fluid flow
Oscillating flow
Particle image velocimetry
Ships
Velocity measurement
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Summary: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.
ISSN:0001-1452
1533-385X
DOI:10.2514/1.J057468