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Aerodynamic design of the scaled supersonic experimental airplane
https://jaxa.repo.nii.ac.jp/records/5741
https://jaxa.repo.nii.ac.jp/records/5741f3847805-e1d6-4a94-8305-65c49fef3ba7
名前 / ファイル | ライセンス | アクション |
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63609010.pdf (3.0 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Aerodynamic design of the scaled supersonic experimental airplane | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 航空機設計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 計算流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 揚抗比 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 平面形 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | マッハ数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | アロー翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | アスペクト比 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 摩擦抗力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力抗力 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic aircraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aircraft design | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic characteristic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computational fluid dynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | lift drag ratio | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | planform | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mach number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | arrow wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aspect ratio | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | friction drag | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure drag | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
著者 |
真保, 雄一
× 真保, 雄一× 吉田, 憲司× 岩宮, 敏幸× 高木, 亮治× 松島, 紀佐× Shinbo, Yuichi× Yoshida, Kenji× Iwamiya, Toshiyuki× Takaki, Ryoji× Matsushima, Kisa |
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著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 数理解析部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 数理解析部 | ||||||
著者所属 | ||||||
富士通 スーパーコンピューターシステムエンジニアリング統括部 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Computational Sciences Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Computational Sciences Division | ||||||
著者所属(英) | ||||||
en | ||||||
Fujitsu Ltd. Supercomputer System Engineering Division | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料 en : JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop) 巻 JAXA-SP-06-029E, p. 67-72, 発行日 2007-03-30 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design 航空宇宙技術研究所 19980316-19980317 東京 日本 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design National Aerospace Laboratory 19980316-19980317 Tokyo Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | As a part of the NAL's scaled supersonic experimental airplane program to establish an aerodynamic design system based on Computational Fluid Dynamics (CFD), an aerodynamic configuration with no propulsion system was designed in a two-stage process. First, a baseline configuration was designed using a conventional linear theory. Then, the CFD and a supersonic inverse method were used to refine the wing geometry and to achieve a higher lift-to-drag ratio at a design point of M = 2 and CL = 0.1. A non-linear effect such as body to wind interference and a wing thickness effect were also handled in this phase. By making use of the inverse method, an upper surface of the wing was designed aiming at a natural laminar flow with a flat-type pressure distribution to reduce a friction drag. A wing warp was also adjusted to achieve an optimal load distribution designed by the linear theory to reduce a pressure drag. The designed new wing was evaluated by a Navier-Stokes analysis and an incompressible boundary layer stability code (SALLY code) and was found to have an improved lift-to-drag ratio, with a wider laminar flow regime and smaller friction drag than the initial geometry. Finally, the CFD analysis was compared with supersonic wind tunnel data and was found to be a well validated tool to be used in the design. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0063609010 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-06-029E |