@inproceedings{oai:jaxa.repo.nii.ac.jp:00016195,
 author = {大石, 栄 and 溝端, 一秀 and 湊, 亮二郎 and 高木, 正平 and 東野, 和幸 and 棚次, 亘弘 and Oishi, Sakae and Mizobata, Kazuhide and Minato, Ryojiro and Takagi, Shohei and Higashino, Kazuyuki and Tanatsugu, Nobuhiro},
 book = {平成24年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2012},
 month = {Jan},
 note = {平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, With the aims of creating and validating innovative fundamental technologies for high-speed atmospheric flights, a small-scale supersonic experimental vehicle is being developed as a flying test bed. The configuration M2006 with a cranked-arrow main wing and twin engines was designed and its aerodynamic characteristics were verified through wind-tunnel and flight tests. A new configuration M2011 with a main wing and tails of similar shapes and a single GG-ATR engine was proposed. Intensive wind-tunnel tests were carried out in transonic and supersonic regimes. It was found that the overall drag coefficient increases as the intake passage is throttled and that the airflow through the intake seems to be squeezed by the development of the boundary layer. In addition, the tail steering box located at the vertical tail root has little influence on overall drag., 形態: カラー図版あり, 形態: PDF, Physical characteristics: Original contains color illustrations, Physical characteristics: PDF, 資料番号: AA0061856059, レポート番号: STCP-2012-059},
 publisher = {宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {小型超音速飛行実験機の風洞試験に基づく機体抗力検討},
 year = {2013}
}