Computations of Active Open-Loop Flow Control on a Fluttering Wing

Fully coupled CFD-CSD simulations are used to characterize the dynamic aeroelastic behavior of a torsionally flexible, finite aspect ratio NACA0018 wing. The main aeroelastic instability, which is also known as stall flutter, is a cycle from increasing angle of attack, large lift, then flow separation and a reduction of the angle of attack due to the elastic forces in the wing. The same sequence of events happens for negative angles of attack. This dynamic instability is a very periodic limit cycle oscillation. A single blowing port was integrated in the wing to control the lift oscillation. Constant blowing at various amplitudes had significant impact, reducing the limit cycle amplitude. The data was used to develop a simple model of the damping added to the structural dynamics due to the forcing. The model showed that the response to forcing is highly nonlinear and that a optimum blowing strength exists.

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