主催: 一般社団法人 日本機械学会
会議名: 2018年度 年次大会
開催日: 2018/09/09 - 2018/09/12
Separation control of NACA0015 airfoil by means of plasma actuators was investigated. Plasma actuators in spanwise array on the suction surface of the airfoil were activated giving temporal periodic disturbances with spanwise phase variations φ = 0 or φ = π in the case of dimensionless burst frequency F+ = 6 and F+ = 0.5 at Re = 63000. The lift and drag of the airfoil were measured using a two-component force balance. The flow around the airfoil was measured by two-component PIV. In the condition of F+ = 6 and φ = π at around stall angle, i.e. 10 degrees, the lift-to-drag ratio was higher than that of F+ = 6 and φ = 0, and the stall angle has extended by 2 degrees. In the most significant case, which is 12 degrees, lift coefficient in the case of F+ = 6 and φ = π improved by approximately 4.9% compared to the case of F+ = 6 and φ = 0. Therefore, it was confirmed that aerodynamic characteristics of the airfoil improved by temporal periodic disturbances with spanwise phase variations and it is expected that the improvement is attributed to the vortex structures, which are called “chain-link-fence structures”.