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Transonic Airfoil Design of Full Potential Flow II. Development of the FORTRAN Code
https://jaxa.repo.nii.ac.jp/records/44930
https://jaxa.repo.nii.ac.jp/records/449301763a55a-99bb-4bb7-9d8f-058c8808f8bf
名前 / ファイル | ライセンス | アクション |
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naltr00673.pdf (5.2 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Transonic Airfoil Design of Full Potential Flow II. Development of the FORTRAN Code | |||||
言語 | ||||||
言語 | eng | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル | ||||||
その他のタイトル | 完全ポテンシャル流の遷音速翼型設計Ⅱ.汎用プログラムの開発 | |||||
著者 |
石黒, 登美子
× 石黒, 登美子× 神谷, 信彦× 河合, 伸坦× 小口, 慶子× ISHIGURO, Tomiko× KAMIYA, Nobuhiko× KAWAI, Nobuhiro× OGUCHI, Keiko |
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著者所属 | ||||||
航空宇宙技術研究所計算センター | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第二部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第二部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所計算センター | ||||||
著者所属(英) | ||||||
en | ||||||
Computer Center, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Second Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Second Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Computer Center, National Aerospace Laboratory(NAL) | ||||||
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報告 en : Technical Report of National Aerospace Laboratory TR-673 巻 673, p. 95, 発行日 1981-05 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The Purpose of Part II of the paper is to present a user’s manual for the FORTRAN program which is coded following the numerical procedure developed for design of transonic airfoils. This procedure, described in Part I, has the following characteristics: 1)It can solve the inverse problem irrespective of the presence of shock waves. 2)The airfoil geometry is designed so that the width of the trailing edge is the required one. 3)The boundary layer calculation is included in this procedure: An actual airfoil geometry is obtained by subtracting a displacement thickness of a boundary layer from an airfoil geometry. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: NALTR0673000 | |||||
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 TR-673 |