@inproceedings{oai:jaxa.repo.nii.ac.jp:00004018,
 author = {丹野, 英幸 and 佐藤, 和雄 and 小室, 智幸 and 伊藤, 勝宏 and 藤田, 和央 and Tanno, Hideyuki and Sato, Kazuo and Komuro, Tomoyuki and Itoh, Katsuhiro and Fujita, Kazuhisa},
 book = {宇宙航空研究開発機構特別資料: 第45回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2013論文集, JAXA Special Publication},
 month = {Mar},
 note = {第45回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2013 (2013年7月4日-5日. タワーホール船堀), 東京, 45th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2013 (July 4-5, 2013. Tower Hall Funabori), Tokyo, Japan, High-temperature real-gas effect was experimentally studied in the free-piston shock tunnel HIEST. A wind tunnel test campaign for aerodynamic measurement with a blunted cone was performed. Free-flight aerodynamic force measurement technique, which was developed especially for HIEST was applied. In this measurement, a model-onboard miniature data recorder was instrumented on the model to store the measured acceleration and pressure records. Three-component aerodynamics coefficient were successfully obtained includes free-stream Pitot pressure at angle of attack from 14 to 32 degree. Under the low enthalpy condition, the present measurements agreed well with the measurements obtained in the conventional hypersonic wind tunnel JAXA-HWT2. It was also observed that the pressure-center of the model moved forward remarkably under the high enthalpy flow condition. It was believed that the shift of pressure-center was caused by high-temperature real-gas effect, 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062268018, レポート番号: JAXA-SP-13-011},
 pages = {99--102},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {実在気体気流条件での空力係数の計測},
 volume = {JAXA-SP-13-011},
 year = {2014}
}