Numerical Investigation of Dynamic Stall Suppression with Steady-Blowing Jet

Abstract

Flow separation can be controlled by providing additional momentum into a separating boundary layer. In this study, steady-blowing jet is applied to a stalled airfoil on the suction side close to the leading edge. It is anticipated that the performance of the separation control depends on the interaction between the jet and the boundary layer. One critical parameter, which impacts on the jet and boundary layer interaction, is the jet angle. Two jet angles are investigated in this study: tangential and chord-normal angles. The rotor airfoil OA209 is simulated with rotor-relevant flow conditions. The current study indicates the tangential jet is more efficient in suppressing dynamic stall, compared to the chord-normal jet for a given jet momentum.