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JAXA高揚力装置半裁模型の風洞試験と空力特性
https://jaxa.repo.nii.ac.jp/records/5634
https://jaxa.repo.nii.ac.jp/records/56343c7a4694-5ee7-4323-8964-e0c166fe0ba7
名前 / ファイル | ライセンス | アクション |
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63742028.pdf (800.2 kB)
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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 | ||||||
タイトル | JAXA高揚力装置半裁模型の風洞試験と空力特性 | |||||
言語 | ||||||
言語 | jpn | |||||
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 | 風洞模型 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 高揚力装置 | |||||
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 | 旅客機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 風洞試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 低速風洞 | |||||
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 | 境界層遷移 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界層剥離 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ナセル | |||||
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 | wind tunnel model | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | high-lift device | |||||
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 | passenger aircraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wind tunnel test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | low speed wind tunnel | |||||
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 | boundary layer transition | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary layer separation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | nacelle | |||||
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 | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Aerodynamics of JAXA high-lift configuration transport model in lowspeed wind tunnel testing | |||||
著者 |
横川, 譲
× 横川, 譲× 村山, 光宏× 伊藤, 健× 山本, 一臣× Yokokawa, Yuzuru× Murayama, Mitsuhiro× Ito, Takeshi× Yamamoto, Kazuomi |
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著者所属 | ||||||
宇宙航空研究開発機構 航空プログラムグループ | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 航空プログラムグループ | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 航空プログラムグループ | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 航空プログラムグループ | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Aviation Program Group | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Aviation Program Group | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Aviation Program Group | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Aviation Program Group | ||||||
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: 第39回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2007論文集 en : JAXA Special Publication: Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007 巻 JAXA-SP-07-016, p. 172-177, 発行日 2008-02-29 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | This report presents experimental data obtained in lowspeed wind tunnel testing for high-lift configuration aircraft model JSM (JAXA Standard Model). Two time of the testing were conducted at 6.5 m by 5.5 m Low-speed Wind Tunnel in JAXA (JAXA-LWT1) aiming to store validation data for CFD (Computational Fluid Dynamics) analysis and to observe flow physics on high-lift system. JSM is a half type model which assumes 17 percent similarity of a modern 100-passenger class regional jet airliner. The model is equipped with leading edge slat, double-slotted flap at the inboard and single-slotted flap at the outboard, flow-through nacelle, in addition, a circular fuselage and Flap Track Fairings (FTF) so that the detailed flow fields occurring in actual aircraft can be provided. At first, repeatability and sensitivity of the force and the moment data in the case the detail of the model was slightly changed were assessed as well as the accuracy was confirmed from large amount of data in the first and the second testing. Variation in lift performances between long-cowling nacelle and short-cowling nacelle was observed with couple of the measurements and visualizations. The results showed much better stall performances of the short-cowling configuration than the long-cowling one that was due to less interference between the nacelle pylon and the wing. Boundary layer tripping on flap could clarify the loss in aerodynamic performances. Finally, improvement of stall characteristics by a vortex generator and an efficient way to decide its installation location by the application of Kriging based Genetic Algorithm (GA) on nacelle was 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: AA0063742028 | |||||
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-07-016 |