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Energies 2020, 13, 1374 16 of 20 " N? $ & Finally, Figure 22 also shows that, in the outer tested sections, the plasma-on and -off separation points coincide or are very close to each other, indicating that even if the actuator influences the flow over the whole wing, its major effects are on the central sections. Therefore, removing the outer tips of the exposed electrode (the ones corresponding to the already attached flow sections) may lead to a similar overall performance, reducing the power consumption of the DBD device. Table 1. Off-to-on chordwise shift of separation vs. spanwise position z: The origin is at the intersection of leading edge and tunnel centerline. # # ? # # 3.3. Actuator Effectiveness Figure 22. Sketch of the separated region for α = 14.5◦ and U∞ = 30 m/s. PIV Plane TA TB TC TD TE Spanwise Position Separation Shift (mm) (z/c) (z/S) (mm) (x/c) 0.073 0.093 0.067 0.030 0.000 2=I=.. 2=I= 54.0 0.18 126.0 0.42 162.0 0.54 234.0 0.78 270.0 0.90 0.058 22.0 0.135 28.0 0.174 20.0 0.252 9.0 0.290 0.0 In the previous sections, some three-dimensional results were presented through the analysis of the separation line. In particular, this allowed to observe that the separated region sensitive to the actuator effect lies in the central part of the model. Instead, the lateral sections are only marginally influenced, suggesting that two electrodes of shorter span can presumably give a similar overall effect requiring lower power, thus improving the device efficiency. Recalling that the passive effects of the actuator are weak, the flow field over the whole model can be considered to remain almost the same with a shorter DBD. The original actuator has 22 tips, and the results analysis suggests to remove 8 of them, corresponding to the 4 outer ones on each side over which the flow is attached. In this way, the actuator length and power consumption would diminish up to 36%, namely the initial W0 = 167 W read in bench tests (Section 2) would be lowered to W1 = 106 W. To determine the capabilities of the actuator in a realistic application, it is desirable to compare the power consumption W with the variations of aerodynamics forces and useful power. Considering the possible effects of lift increase ∆L and drag reduction ∆D, two effectiveness parameters ∆L/W and ∆D/W could be introduced, with dimension N/W. Correspondingly, two dimensionless efficiencies could be formally introduced: (1) by considering a wing lifting a given load with vertical velocity Vt, the lifting power is LVt and the (lifting power increment)/(electric power) ratio is ∆LVt/W; (2) considering the drag reduction, the corresponding (power saving)/(electric power) ratio is ∆D U∞/W. The complete determination of the above parameters would require values of lift and drag, with the drag typically affected by a larger uncertainty. These forces are not directly readablePDF Image | Stall Control by Plasma Actuators: Characterization along the Airfoil Span
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