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一様流中に大きな角度で吹き出したジェットの径路と誘導速度場
https://jaxa.repo.nii.ac.jp/records/44590
https://jaxa.repo.nii.ac.jp/records/4459001118dd2-3eca-480f-aecd-6cf9d2adcb31
名前 / ファイル | ライセンス | アクション |
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naltr00343.pdf (2.1 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 | ||||||
タイトル | 一様流中に大きな角度で吹き出したジェットの径路と誘導速度場 | |||||
言語 | ||||||
言語 | jpn | |||||
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(英) | ||||||
その他のタイトル | Path and Induced Field of a Jet Exhausting at a Larger Angle into a Uniform Cross Flow | |||||
著者 |
遠藤, 浩
× 遠藤, 浩× 中谷, 輝臣× 飛田和, 茂× 桑野, 尚明× 戸田, 亘洋× ENDO, Hiroshi× NAKAYA, Teruomi× HIDAWA, Shigeru× KUWANO, Naoaki× TODA, Nobuhiro |
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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空気力学第二部 | ||||||
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 | ||||||
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 | ||||||
Second Aerodynamics Division, 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-343 巻 343, p. 25, 発行日 1973-10 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A semi-empirical method is presented in this paper to calculate the path and the induced velocity of a round turbulent jet exhausting into a uniform cross flow. By analogy with a suction cylinder and based on a vortex-sheet theory developed in the previous paper, the jet is replaced by a vortex-doublet which is an idealized representation of the trailing vortex-sheet on the surface of the jet, the induced velocity around the jet being assumed as induced by the vortex-doublet. The comparison of calculated downwash and sidewash angles of the induced flow with experimental results obtained in 6M low-speed wind tunnel of NAL, it is proved that the present method can be used as a working basis for investigating the interaction with the airframe of a jet-lift VTOL aircraft through the far induced field of exhaust gas. | |||||
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: NALTR0343000 | |||||
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-343 |