@inproceedings{oai:jaxa.repo.nii.ac.jp:00014439,
 author = {松野, 隆 and 太田, 健太郎 and 金村, 玄太 and 荒堀, 宏典 and 岩田, 博 and 川添, 博光 and 藤井, 孝蔵 and Matsuno, Takashi and Ota, Kentaro and Kanemura, Kenta and Arahori, Hironori and Iwata, Hiroshi and Kawazoe, Hiromitsu and Fujii, Kozo},
 book = {宇宙航行の力学シンポジウム, Symposium on Flight Mechanics and Astrodynamics},
 month = {Dec},
 note = {宇宙航行の力学シンポジウム(平成20年度)(2008年12月4～5日、宇宙航空研究開発機構宇宙科学研究本部), Symposium on Flight Mechanics and Astrodynamics 2008 (December 4-5, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan, A Plasma-induced active flow control device in low supersonic flow is studied experimentally. A plasma flow actuator, which consists of a single dielectric barrier discharge(SDBD) plasma generator, was developed and tested in the supersonic wind tunnel at ISAS/JAXA with Mach1.7 flow. Experiments with high speed Schlieren visualization have been carried out to evaluate the feasibility of plasma actuator displace shock waves in front of the actuators., 資料番号: AA0064729016},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {プラズマを用いた超音速剥離流れの制御},
 volume = {平成20年度},
 year = {2009}
}