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Aerodynamic design of supersonic experimental airplane
https://jaxa.repo.nii.ac.jp/records/5761
https://jaxa.repo.nii.ac.jp/records/5761d17b0ae7-2aab-4cb6-82bc-107abbf6f599
名前 / ファイル | ライセンス | アクション |
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63609030.pdf (2.1 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 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 | 実験機 | |||||
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 | 胴翼構成 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力設計 | |||||
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 | 翼平面形 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界層遷移 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 設計最適化 | |||||
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 | research aircraft | |||||
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 | body-wing configuration | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic 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 | wing planform | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary layer transition | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure distribution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | design optimization | |||||
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 |
岩宮, 敏幸
× 岩宮, 敏幸× 吉田, 憲司× 真保, 雄一× 牧野, 好和× 松島, 紀佐× Iwamiya, Toshiyuki× Yoshida, Kenji× Shinbo, Yuichi× Makino, Yoshikazu× 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 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
富士通 | ||||||
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 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
Fujitsu Ltd. | ||||||
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. 274-279, 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ワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ 航空宇宙技術研究所 20000117-20000119 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 Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport National Aerospace Laboratory 20000117-20000119 Tokyo Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | In the first stage of the NAL's experiment for supersonic transport (NEXST-1: Next generation Supersonic Transport-l) project, the aerodynamic design has focused on the of drag at a supersonic cruising speed with a clean wing-body configuration by using Computational Fluid Dynamics (CFD). In the course of design process, four aerodynamic concepts have been applied; (1) arrow-type planform design (2) warped wing (3) area-ruled body (4) a Natural Laminar Flow (NLF) wing. (1) and (2) are effective for the reduction of drag due to lift while (3) is effective the reduction of wave drag due to volume. They are the concepts based on the linear theory. The concept (4) is devised for the reduction of the friction drag. The application of the NLF concept to the SST (SuperSonic Transport) configuration has no previous instance and an original trial. For the realization of the NLF wing at supersonic cruising speed, we first designed a pressure distribution on the wing and then applied an inverse design method based on the supersonic small perturbation equation. After less than 10 design cycles, we obtained satisfactory design result which display a good agreement with target pressure. The transition position was evaluated by an incompressible boundary layer stability code (SALLY code) and compressible boundary layer stability code (LSTAB code), the latter of which was developed in NAL. The evaluation revealed that the turbulence transition characteristics are good. | |||||
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: AA0063609030 | |||||
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 |