Abstract
The flow over an OA209 airfoil subjected to a sinusoidal pitching motion under dynamic stall conditions and equipped with an innovative deployable vortex generator actuator inducing stall control is experimentally and numerically investigated. Pressure and time-resolved particle image velocimetry measurements allow a detailed comparison to be performed between clean and controlled cases, including separation point detection and proper orthogonal decomposition analysis. Along with wind tunnel testing, numerical simulations are performed by solving the unsteady Reynolds-averaged Navier–Stokes equations with the ONERA elsA code. Computations are successfully compared to the experimental reference and bring further understanding of the deployable vortex generator actuation.
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