@inproceedings{oai:jaxa.repo.nii.ac.jp:00002936,
 author = {森, 直紀 and 渡邉, 保真 and 鈴木, 宏二郎 and Mori, Naoki and Watanabe, Yasumasa and Suzuki, Kojiro},
 book = {宇宙航空研究開発機構特別資料: 第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 50th Fluid Dynamics Conference / the 36th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム (2018年7月4日-6日. 宮崎市民プラザ), 宮崎市, 宮崎, 50th Fluid Dynamics Conference /the 36th Aerospace Numerical Simulation Symposium (July 4-6, 2018. Miyazaki Citizen's Plaza), Miyazaki, Japan, In recent years, the flow control method using plasma discharge, for example, a plasma actuator, has been attracting attention, because of its shorter response-time than conventional mechanical control devices such as flaps. In this study, a flat plate model with a small cavity under the surface was tested for the discharge experiment in the Mach 7 hypersonic wind tunnel in Kashiwa campus, the University of Tokyo. Two types of the discharge cavities were tested: a cavity with an orifice normal to the surface and a cavity with an orifice and a forward-facing-step inlet open to the boundary layer flow. A pair of tungsten rod-type electrodes were inserted into the cavity, and the applied voltage was 1kV at maximum using high-power capacitors. The discharge occurred intermittently and the time history of the discharge voltage was measured. The effect of the discharge on the flow field was visualized by the schlieren method. In the case of the intake moved slightly forward when the discharge occurred., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1830029007, レポート番号: JAXA-SP-18-005},
 pages = {103--106},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {模型表面内側に設けた放電室による極超音速境界層流れ制御の基礎実験},
 volume = {JAXA-SP-18-005},
 year = {2019}
}