Flow Control around NACA0015 Airfoil Using a Dielectric Barrier Discharge Plasma Actuator over a Wide Range of the Reynolds Number
Satoshi Sekimoto,
Kozo Fujii,
Masayuki Anyoji,
Yuma Miyakawa,
Shinichiro Ito,
Satoshi Shimomura,
Hiroyuki Nishida,
Taku Nonomura,
Takashi Matsuno
Affiliations
Satoshi Sekimoto
Department of Mechanical Systems Engineering, Faculty of Engineering, Tokyo University of Agriculture and Technology, Koganei 184-8588, Japan
Kozo Fujii
Department of Information and Computer Technology, Faculty of Engineering, Tokyo University of Science, Tokyo 125-8585, Japan
Masayuki Anyoji
Department of Advanced Environmental Science and Engineering, Interdisciplinary Graduate School of Engineering Sciences, Faculty of Engineering Sciences, Kyushu University, Fukuoka 816-8580, Japan
Yuma Miyakawa
Department of Mechanical Engineering, Faculty of Engineering, Kogakuin University, Hachioji 192-0015, Japan
Shinichiro Ito
Department of Mechanical Engineering, Faculty of Engineering, Kogakuin University, Hachioji 192-0015, Japan
Satoshi Shimomura
Department of Mechanical Systems Engineering, Faculty of Engineering, Tokyo University of Agriculture and Technology, Koganei 184-8588, Japan
Hiroyuki Nishida
Department of Mechanical Systems Engineering, Faculty of Engineering, Tokyo University of Agriculture and Technology, Koganei 184-8588, Japan
Taku Nonomura
Department of Aerospace Engineering, Faculty of Engineering, Tohoku University, Sendai 980-8578, Japan
Takashi Matsuno
Department of Engineering, Faculty and Graduate School of Engineering, Tottori University, Tottori City 680-8552, Japan
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.
