@inproceedings{oai:jaxa.repo.nii.ac.jp:00003501,
 author = {後藤, 駿 and 金崎, 雅博 and 村山, 光宏 and 伊藤, 靖 and 山本, 一臣 and Goto, Shun and Kanazaki, Masahiro and Murayama, Mitsuhiro and Ito, Yasushi and Yamamoto, Kazuomi},
 book = {宇宙航空研究開発機構特別資料: 第48回流体力学講演会/第34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 48th Fluid Dynamics Conference / the 34th Aerospace Numerical Simulation Symposium},
 month = {Dec},
 note = {第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム (2016年7月6日-8日. 金沢歌劇座), 金沢市, 石川, 48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan, To develop next generation aircrafts, the remarkable improvement of the economic efficiency such as fuel burn, environmental performance and the comfortability for passengers has been requested. The one of ideas for the next generation aircraft is the one which has a wide fuselage with upper mounted engines. This kind of aircraft has possibility to improve the aerodynamic performance by the optimum inlet flow. In this paper, the aerodynamic performance of the wide fuselage aircraft was investigated with deforming the fuselage geometry and displacing the engine nacelle. The intake/ exhaust flow is also simulated. According to investigation results, the design knowledge which achieved higher lift-to-drag ratio could be found out. In addition, it was also found that the lift was increased by the intake flow. These results suggested that the over-the-fuselage engine concept has possibility to be next generation civil aircraft which could improve the fuel economy and the environmental performance., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630031026, レポート番号: JAXA-SP-16-007},
 pages = {189--194},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {機体後部上方エンジンマウント幅広胴体の尾部設計と空力性能評価},
 volume = {JAXA-SP-16-007},
 year = {2016}
}