@inproceedings{oai:jaxa.repo.nii.ac.jp:00046347,
 author = {甲斐, 大貴 and 杉浦, 裕樹 and 手塚, 亜聖 and Kai, Daiki and Sugiura, Hiroki and Tezuka, Asei},
 book = {宇宙航空研究開発機構特別資料: 第51回流体力学講演会/第37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 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム (2019年7月1日-3日. 早稲田大学早稲田キャンパス国際会議場), 新宿区, 東京, 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium (July 1-3, 2019. International Conference Center, Waseda University), Shinjuku-ku, Tokyo, Japan, Forced oscillation wind tunnel tests were conducted on a delta wing model with a 60 deg swept leading edge using JAXA's 60 cm high angle of attack (AOA) magnetic suspension and balance system (MSBS) wind tunnel. The pitch axis dynamic derivatives of the model were measured, and the effects of the center AOA of oscillation, oscillation amplitude, and oscillation frequency were surveyed. The loci of the aerodynamic longitudinal components varied complexly according to oscillation center AOA, amplitude, and frequency; however, in cases of oscillation center AOA of 0 degree and frequency of 1 Hz, the loci of pitching moment tended to vary in similar form with increase of the oscillation amplitude. The degree of scatter of the dynamic derivatives tended to be larger at higher angles of attack., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1930011006, レポート番号: JAXA-SP-19-007},
 pages = {107--112},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {磁力支持天秤装置による運動するデルタ翼機模型の非定常空力計測},
 volume = {JAXA-SP-19-007},
 year = {2020}
}