Flow control experiments on a NACA 0015 airfoil using pulsed vortex generator jets (PVGJs) are carried out at a chord-based Reynolds number of \(4.6 \times 10^5\). Configurations of partially separated flow over the airfoil are studied with a special focus on the transient effects induced by actuation. The main objective is the improvement of the rate of variation of the aerodynamic loads. The response to a single-pulse actuation, of duration smaller than the convective time over the airfoil, is compared with the response to the onset of steady blowing. We observe that the single-pulse actuation, if correctly tuned, induces a higher rate of loads variation (up to 50 \(\%\) for the lift). By using Lagrangian analyzing tools (finite-time Lyapunov exponent—FTLE), we show that this improvement is due to dynamical effects at the scale of the airfoil, associated with the formation of a closed separation region during the initial transient phase after the end of actuation. Such load control could be effective in situations where a fast time response is needed to compensate unsteady aerodynamic effects, such as in gusting flows or during rapid maneuvers.
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This work is supported by Direction Générale de l’Armement (DGA) and the CPER FEDER project of Région Nouvelle Aquitaine. The authors gratefully acknowledge the valuable technical support of Jean-Marc Breux, François Paille, Patrick Braud, Romain Bellanger, Bastien Robert, and Mathieu Rossard during the experiments.
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Carusone, A., Sicot, C., Bonnet, JP. et al. Transient dynamical effects induced by single-pulse fluidic actuation over an airfoil. Exp Fluids 62, 25 (2021). https://doi.org/10.1007/s00348-020-03108-0