- 著者
- 南海 昂輝 鈴木 健人 小室 淳史 野々村 拓 浅井 圭介
- 出版者
- 一般社団法人 日本機械学会
- 雑誌
- 年次大会 2019 (ISSN:24242667)
- 巻号頁・発行日
- pp.S05212, 2019 (Released:2020-03-25)
A linear reduced-order model of flow fields around an airfoil controlled by a plasma actuator is constructed based on experimental data. An alternating-current dielectric-barrier-discharge plasma actuator (ac-DBDPA) with random input was used to control flow fields around a NACA0015 airfoil at the chord Reynolds number of 6.4 × 104 in a wind tunnel testing and time-resolved data of the velocity fields were obtained by particle image velocimetry. Proper orthogonal decomposition (POD) was employed to the data and the lower-dimensional description of them was obtained by using the first ten POD modes. Subsequently, the least-squares method was applied to the time history of the POD modes and the control input corresponding to the voltage amplitude of ac-DBDPA, and the coefficient matrix of the linear model was computed. The effects of the control input on the velocity fields reconstructed by the POD modes were investigated from the input matrix. It is shown that the velocity fields are not influenced much when the average value of the input is changed. On the other hand, they are sensitive to the input change. This result corresponds to the fact that the intermittent actuation is effective for the flow control by plasma actuators such as the burst-mode actuation or nanosecond-pulse-driven DBDPA.
