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設計における数値解析の活用について その15:SSTの主翼空力設計
https://jaxa.repo.nii.ac.jp/records/37139
https://jaxa.repo.nii.ac.jp/records/3713981e7d971-d7ce-4813-9f12-d91901a5ccd9
名前 / ファイル | ライセンス | アクション |
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nalsp0037013.pdf (758.0 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 | 設計における数値解析の活用について その15:SSTの主翼空力設計 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | SST | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速輸送機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 主翼空力設計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 小型高速実験機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 高揚抗比 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 抗力低減 | |||||
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 | CFD | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 非構造格子 | |||||
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 | 安定性解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 低アスペクト比翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 翼胴形状 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 逆設計法 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | SST | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic transport | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | main wing aerodynamic design | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | subscaled high speed experimental aircraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | high lift to drag ratio | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | drag reduction | |||||
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 | CFD | |||||
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 | unstructured grid | |||||
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 | stability analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | low aspect ratio wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wing body configuration | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | inverse design method | |||||
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 | Role of CFD in aeronautical engineering. 15: Aerodynamic design of an SST wing | |||||
著者 |
生越, 博景
× 生越, 博景× 嶋, 英志× Ogoshi, Hirokage× Shima, Eiji |
|||||
著者所属 | ||||||
川崎重工業 | ||||||
著者所属 | ||||||
川崎重工業 | ||||||
著者所属(英) | ||||||
en | ||||||
Kawasaki Heavy Industries LTD | ||||||
著者所属(英) | ||||||
en | ||||||
Kawasaki Heavy Industries LTD | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory (NAL) | |||||
書誌情報 |
航空宇宙技術研究所特別資料 en : Special Publication of National Aerospace Laboratory 巻 37, p. 81-86, 発行日 1998-02 |
|||||
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 | 航空宇宙技術研究所 12-13 Jun. 1997 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 | National Aerospace Laboratory 12-13 Jun. 1997 Tokyo Japan | |||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | NAL(航空宇宙技術研究所)の小型無人実験機の翼をL/D(揚抗)比を高めるように設計した。特に、全抗力のほとんど半分を占める翼部分の摩擦抗力を低減するように設計した。この目的のため、UG3(3次元非構造格子CFD(数値流体力学)ソルバ)およびSALLY(3次元層流境界層安定性解析コード)を用いて、出来るだけ層流を保つようにして、翼部分を設計した。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The wing of the sub-scaled unmanned experimental aircraft of NAL is designed to improve the L/D (Lift to Drag) ratio. The wing section is designed especially to reduce skin friction drag, which amounts to nearly half of the total drag. For this purpose, the wing section was designed to remain laminar flow as far as possible, using UG3 (3D (Three Dimensional) Unstructured Grid CFD (Computational Fluid Dynamics) solver) and SALLY (3D laminar boundary layer stability analysis code). | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0289-260X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10097345 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0001433013 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL SP-37 |