![]() ![]() Patel MP, Ng TT, Vasudevan S, Corke TC, He C (2007) Plasma actuators for hingeless aerodynamic control of an unmanned air vehicle. Post M, Corke T (2006) “Separation control using plasma actuators: dynamic stall control on an oscillating airfoil. Post ML, Corke TC (2004) Separation control on high angle of attack Airfoil using plasma actuators. Roth JR, Sherman DM, Wilkinson SP “Electrohydrodynamic flow control with a glow-discharge surface plasma”. Roth JR, Sherman DM, Wilkinson SP (1998) Boundary Layer flow control with a one atmosphere uniform glow discharge surface plasma. AIAA J 40(5):1015–1018Ĭorke TC, Post ML, Orlov DM (2009) “Single dielectric barrier discharge plasma enhanced aerodynamics: physics, modeling and applications”. Illinois Institute of TechnologyĬorke TC, Cavalieri DA, Matlis E (2002) Boundary-layer instability on sharp cone at Mach 3.5 with controlled input. J Fluid Mech 219(3):621–633Ĭavalieri D (1995) “On the experimental design for instability analysis on a cone at Mach 3.5 and 0.6 using a corona discharge perturbation method. Kosinov AD, Maslov AA, Shevelkov SG (1990) Experiments on the stability of supersonic laminar boundary layers. Gad-El-Hak M (2000) Flow control passive, active, and reactive flow management. To examine the accuracy of the results, aerodynamic coefficients of oscillating airfoil without flow control are validated against numerical and experimental data. It is observed that in the case of oscillatory free stream, the plasma actuator causes an increment in maximum lift coefficient and little delay in the dynamic stall while increasing the mean drag coefficient and lift coefficient hysteresis area. Finally, the free stream oscillation effect on aerodynamic coefficients and plasma actuator performance is discussed. Furthermore, it is observed that the actuator with a 50% duty cycle with lower electric power consumption has almost the same results compared to continuous actuation. In addition, applied voltage and actuation frequency are varied and their effects on aerodynamic coefficients and negative damping coefficient are investigated. Then the effect of actuator location over the suction side of the airfoil on aerodynamic performance is studied and leading-edge is selected as the optimal location. The effect of the plasma actuator on the pitching moment coefficient hysteresis and negative aerodynamic damping coefficient is also investigated. It is observed that the plasma actuator increases mean lift, decreases mean drag, reduces lift coefficient hysteresis, and delays separation. The plasma actuator effect is added to momentum equations as a body force using a phenomenological model. Airfoil is oscillating beyond static stall angle and experiences deep dynamic stall. Flow is considered two-dimensional, incompressible, and turbulent at a Reynolds number of 135,000, which is equivalent to the flow around wind turbine blades. In this study, DBD plasma actuators’ effect on the flow over a pitching NACA 0012 airfoil is investigated. ![]()
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