Flow Control around NACA0015 Airfoil Using a Dielectric Barrier Discharge Plasma Actuator over a Wide Range of the Reynolds Number

• DOI: 10.3390/act12010043
• Publication Date: 2023-01-16T09:57:19Z
• Authors: Satoshi Sekimoto; Kozo Fujii; Masayuki Anyoji; Yuma Miyakawa; Shinichiro Ito; Satoshi Shimomura; Hiroyuki Nishida; Taku Nonomura; Takashi Matsuno
• Keywords: TK1001-1841; Production of electric energy or power. Powerplants. Central stations; wide range of Reynolds number; 0103 physical sciences; TA401-492; NACA0015 airfoil; plasma actuator; NACA0015 airfoil; wind tunnel experiment; wide range of Reynolds number; wind tunnel experiment; Materials of engineering and construction. Mechanics of materials; 01 natural sciences; plasma actuator

In this study, an experimental investigation of separation control using a dielectric barrier discharge plasma actuator was performed on an NACA0015 airfoil over a wide range of Reynolds numbers, angles of attack, and nondimensional burst frequencies. The range of the Reynolds number was based on a chord length ranging from 2.52 × 105 to 1.008 × 106. A plasma actuator was installed at the leading edge and driven by AC voltage. Burst mode (duty-cycle) actuation was applied, with the nondimensional burst frequency ranging between 0.1–30. The control authority was evaluated using the time-averaged distribution of the pressure coefficient Cp and the calculated value of the lift coefficient Cl. The baseline flow fields were classified into three types: (1) leading-edge separation; (2) trailing-edge separation; and (3) the hysteresis between (1) and (2). The results of the actuated cases show that the control trends clearly depend on the differences in the separation conditions. In leading-edge separation, actuation with a burst frequency of approximately F+= 0.5 creates a wide negative pressure region on the suction-side surface, leading to an increase in the lift coefficient. In trailing-edge separation, several actuations alter the position of turbulent separation.