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Inverse wing design for the scaled supersonic experimental airplane with ensuring design constraints
https://jaxa.repo.nii.ac.jp/records/5763
https://jaxa.repo.nii.ac.jp/records/5763f13a9f26-bab2-443e-9a5a-aeb9e045b131
名前 / ファイル | ライセンス | アクション |
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63609032.pdf (2.2 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 | Inverse wing design for the scaled supersonic experimental airplane with ensuring design constraints | |||||
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 | 翼型設計 | |||||
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 | 圧力分布 | |||||
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 | 積分方程式 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 層流境界層 | |||||
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 | 翼型プロフィル | |||||
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 | wing design | |||||
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 | pressure distribution | |||||
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 | integral equation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | laminar boundary layer | |||||
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 | airfoil profile | |||||
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 |
松島, 紀佐
× 松島, 紀佐× 岩宮, 敏幸× Zhang, Wanqiu× Matsushima, Kisa× Iwamiya, Toshiyuki× Zhang, Wanqiu |
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著者所属 | ||||||
富士通 | ||||||
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(英) | ||||||
en | ||||||
Fujitsu Ltd. | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
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. 286-291, 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 | Aerodynamic shape of a wing for NAL (National Aerospace Laboratory)'s first SST (SuperSonic Transport) model has been designed by a supersonic inverse design method. This method handles wing-fuselage configurations and provides wing section's geometry at every span for Navier-Stokes flowfields. The design target is a NLF (Natural Laminar Flow) wing at the speed of M(sub infinity) = 2.0. The original system of the inverse design method has to be modified so that several design constraints can be satisfied. By means of the method, a wing section shape which has much more desirable characteristics has been designed than that by the traditional design method. In terms of aerodynamics to realize a NLF wing, the modified method works very well. The pressure distribution of the designed wing shows good agreement with the target pressure. In terms of constraints, most of them can be satisfied by using the modified design method; however, difficulty has been found during the process for thickness constraint control. The prospective strategy to cope with the thickness constraint is discussed. | |||||
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: AA0063609032 | |||||
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 |