@inproceedings{oai:jaxa.repo.nii.ac.jp:00047324,
 author = {藤林, 大晶 and 大関, 義弘 and 手塚, 亜聖 and FUJIBAYASHI, Hiroaki and OZEKI, Yoshihiro and TEZUKA, Asei},
 book = {宇宙航空研究開発機構特別資料: 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2020オンライン論文集, JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online},
 month = {Feb},
 note = {流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2020オンライン (2020年9月28日-30日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議), Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting), Transient response from attached to separated boundary layer on a NACA0012 airfoil at the angle of attack of 1.5 deg with vortices induced by a dielectric barrier discharge plasma actuator (PA) was investigated experimentally. The PA was attached on the surface of the airfoil at 65% of the chord length from the leading edge, and the Reynolds number based on the airfoil chord was 5×10(exp 4). The height of separated flow from the airfoil was estimated using visualized flow images. When the PA was operated at the burst frequency of 100 Hz, the height became quasi-steady for 50-60 ms after the begging of the PA driven, and the height became quasi-steady for 150 ms after the PA stopped. Considering these transient responses of the separated boundary layer, the PA was driven with the way which alternatively repeats continuous N times burst actuation and T ms stop. We compared the lift coefficient when the PA driven with the way and the lift coefficient when the PA driven with the burst actuation., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030013003, レポート番号: JAXA-SP-20-008},
 pages = {19--26},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {プラズマアクチュエータの間欠的バースト駆動による駆動時間削減と空力性能改善},
 volume = {JAXA-SP-20-008},
 year = {2021}
}