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Energies 2020, 13, 1374 15 of 20 = > 1 # 0.5 0 -0.5 -1 -1.5 -2 # # N? N? # # +F +F +F +F # # +F +F +F +F +F +F # +F +F Figure21.CP valuesat(a)TA,(b)TB,and(c)TC forα=14.5◦ andU∞ =30m/s. # N? With a further elaboration of the PIV data, the location and displacement of the separation points has been estimated for all the analyzed sections. This allowed to obtain a representation of the complete three-dimensional separation line over the whole airfoil span both for plasma-on and -off configurations, as reported in Figure 22 and Table 1. A more refined scan, based on a large number of PIV planes, would lead to a similar shape but includes a superimposed undulation, which is due to the tip-root differences previously described. The plasma-off separation line (blue line in figure) shows the classical contour for a finite wing [23,25]; that is expected to appear also in a wind tunnel test if, as in this experiment, large end plates are not introduced. Under the actuator effect, the separation line (red line) retains a very similar shape but is completely shifted downstream. This displacement may seem mild, but the involved area is quite wide and affects a region where the pressure changes on the model surface can lead to a significant lift variation. Further studies could be done investigating possible enhancements of the control authority: after optimizing the actuator for a given airspeed (Section 2) and setting the same supply to avoid an increase of power consumption, there is the chance to change the DBD location, keeping in mind that the actuation must always take place upstream of the separation, as proven in Reference [33,34]. This would lead to placing the actuator upstream around the airfoil nose, affecting the flow also in the accelerated zone between the stagnation and the nose itself, and could give rise to further developments. ?PDF Image | Stall Control by Plasma Actuators: Characterization along the Airfoil Span
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