Autonomous Sensing and Control of Wing Stall Using a Smart Plasma Slat

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Autonomous Sensing and Control of Wing Stall Using a Smart Plasma Slat ( autonomous-sensing-and-control-wing-stall-using-smart-plasma )

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PATEL ET AL. 525 Fig. 17 Comparison of PASC controller response during the NACA 0015 pitch-up experiment using 4-bin 4-threshold (left) and 8-bin 4-threshold (right) settings. Fig. 18 Comparison of PASC controller response during the NACA 0015 pitch-up (left) and pitch-down (right) experiments using different bin and threshold settings. stall hysteresis and on lift and drag. The results from these experiments are highlighted in Fig. 21, which shows that stall hysteresis was practically eliminated using the PASC-controlled smart plasma slat. Concluding Remarks Two methods of feedback control for the smart plasma slat application were presented. Both use information from pressure fluctuations measured using a single pressure sensor near the leading edge (x=c 􏰓 0:05) of an airfoil. Both methods were demonstrated on a NACA 0015 airfoil that used a leading-edge plasma actuator for separation control. The first method (amplitude peak sense and control) used the detection of a spectral peak in the pressure fluctuations at the unsteady plasma actuator frequency as an indicator of incipient separation. The second method (pressure amplitude sense and control) relied on a smart system that looked at the frequency distribution of energy in the pressure fluctuations to sense incipient separation. In a scenario of decreasing angles of attack from post-stall conditions, where the actuator maintained an attached flow, both feedback control approaches were capable of determining when the flow would naturally reattach, and turned the actuator off. The capabilities of either of the feedback control approaches provide an improvement over simple open-loop control that can conserve flow actuator power in situations where it is limited, or in maximizing the system impact that active flow control can provide.

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