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Stall Control by Plasma Actuators: Characterization along the Airfoil Span

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Stall Control by Plasma Actuators: Characterization along the Airfoil Span ( stall-control-by-plasma-actuators-characterization-along-air )

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Energies 2020, 13, 1374 12 of 20 bubble, diminishing its extension and displacing its center closer to the airfoil. Accordingly, the outer streamlines are deflected toward the airfoil, presumably leading to a decrease of the pressure coefficient and consequently to a lift increase. 􏲓􏲙 O􏲚? 􏲓 􏲘􏲓􏲙 􏲖=􏲗 􏲓􏲙# N􏲚?􏲕 􏲖>􏲗 􏲓􏲙# N􏲚?􏲕 $􏲓 #􏲓 "􏲓 !􏲓 􏲓 􏲒􏲓 􏲓 7􏲖􏲎􏲚I􏲗 􏲒 􏲓 􏲒 􏲓 Figure 15. (a) Plasma-off and (b) plasma-on flow field at TA for α = 14.5◦ and U∞ = 30 m/s. Moving along the span, the next examined tip is TB. The plasma-off condition is reported in Figure 16a, where a natural displacement of the separation point toward the trailing edge is already observed due to the classical three-dimensional flow geometry over the finite wing. Under the plasma effect (Figure 16b) a further shift in the order of 0.1 c is measured, along with a reduction of the recirculation bubble of which the center lays closer to the airfoil. At the same time, the external streamlines are accelerated and deflected closer to the airfoil. Then, even if the three-dimensional flow geometry pushes the natural separation point downstream of the actuator tip position, the actuator still has a good authority on the flow with beneficial effects for the wing performance. 􏲓􏲙 O􏲚? 􏲓 􏲘􏲓􏲙 􏲖=􏲗 􏲒 􏲓􏲙# 􏲓 N􏲚?􏲕 􏲖>􏲗 􏲒 􏲓􏲙# 􏲓 N􏲚?􏲕 $􏲓 #􏲓 "􏲓 !􏲓 􏲓 􏲒􏲓 􏲓 7􏲖􏲎􏲚I􏲗 Figure 16. (a) Plasma-off and (b) plasma-on flow field at TB for α = 14.5◦ and U∞ = 30 m/s. A similar flow field is encountered at TC , with the separation point in the plasma-off configuration already laying within 50% of chord from the trailing edge (Figure 17a) With plasma on (Figure 17b) it is further shifted downstream, influencing a narrower region of the flow. The streamlines are again accelerated and realigned with the airfoil profile, presumably enhancing the lift coefficient also at this station.

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