@inproceedings{oai:jaxa.repo.nii.ac.jp:00048377,
 author = {新井, 陽生 and 荻野, 翔矢 and 金崎, 雅博 and 伊藤, 靖 and 村山, 光宏 and 山本, 一臣 and ARAI, Haruki and OGINO, Shoya and KANAZAKI, Masahiro and ITO, Yasushi and MURAYAMA, Mitsuhiro and YAMAMOTO, Kazuomi},
 book = {宇宙航空研究開発機構特別資料: 第53回流体力学講演会/第39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 53rd Fluid Dynamics Conference / the 39th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第53回流体力学講演会/第39回航空宇宙数値シミュレーション技術シンポジウム (2021年6月30日-7月2日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議), The 53rd Fluid Dynamics Conference / the 39th Aerospace Numerical Simulation Symposium (June 30 - July 2, 2021. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting), The over-the-fuselage-nacelle aircraft has been expected to be a silent aircraft. In the design of this type aircraft, the aerodynamic interference between the nacelles and the fuselage should be reduced for the fuel economy. To investigate the interaction, the flow field surrounded by the nacelles and the fuselage was considered as a nozzle. The relationship between the aperture ratio and the flow separation was investigated. Numerical simulations were carried out for the aircraft with different aperture ratios by deforming the nacelle shape and the fuselage shape. As a result, it was confirmed that there was drag varied by the location of the local shock which influenced the pressure distribution. The simultaneous designs of the fuselage and nacelle were effective to minimize separation., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2130027004, レポート番号: JAXA-SP-21-008},
 pages = {85--94},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Over-the-Fuselage-Nacelle形態機のエンジン-胴体間流路断面積の変化が空力性能に及ぼす影響調査},
 volume = {JAXA-SP-21-008},
 year = {2022}
}