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Energies 2020, 13, 1374 11 of 20 O? = > ! " ! " 7I 7I Figure 13. Cross-wake velocity profiles at TA for (a) α = 22◦ and U∞ = 20 m/s and (b) α = 14.5◦ and U∞ = 35 m/s. Further measures were carried out to find the maximum operational velocity at which the actuator still controls the flow. Its value turned out to be in the 35 to 40 m/s range at α = 14.5◦. The U∞ = 35 m/s case is reported in Figure 14a,b, where a slight shift in the separation point and a reduction in the recirculation bubble are still visible. The flow modifications are better observed comparing the cross-wake velocity profiles reported in Figure 13b. They confirm the wake width reduction effect, and also in this, case the velocity of the two curves is slightly different in the proximity of the trailing edge, i.e., in the upper part of the graph. As previously stated, this is presumably due to the overall effect of the actuator on the circulation. O? = > # N? $ # " ! 7I # N? Figure 14. (a) Plasma-off and (b) plasma-on flow field at TA for α = 14.5◦ and U∞ = 35 m/s. After these validations, the study proceeded with the analysis of the spanwise sections, performed at an intermediate velocity of U∞ = 30 m/s, as anticipated in Section 2. 3.2. Spanwise Sections Analysis at U∞ = 30 m/s, α = 14.5◦ After the setup and actuator authority validation, the actuator effect on the five spanwise sections at U∞ =30 m/s and α = 14.5◦ was analyzed. Since the tip-root difference was already examined in Section 3.1, the measures were performed on the five tip planes TA, TB, TC, TD, TE, reported in Figure 7. During these tests, the cameras were kept fixed, so they captured wider flow fields in correspondence with the outer sections. Therefore, all the images collected for the lateral planes needed to be corrected for the perspective effect through a rescaling. Once again, the central sections were analyzed first. The study of tip TA in the plasma-off configuration (Figure 15a) shows separation at about 20% of the chord whilst the recirculation bubble is extended up to the trailing edge. When the actuator is turned on (Figure 15b) it has a good authority on the flow, leading to a shift in the separation point of about 0.1c and to a reduction of the recirculationPDF Image | Stall Control by Plasma Actuators: Characterization along the Airfoil Span
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