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小型二段式ロケットの前後翼間の空力干渉による垂直力について
https://jaxa.repo.nii.ac.jp/records/45072
https://jaxa.repo.nii.ac.jp/records/4507277326fd0-9e0d-4713-8cbe-f895dd0768cc
名前 / ファイル | ライセンス | アクション |
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naltr00814.pdf (1.2 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 | ||||||
タイトル | 小型二段式ロケットの前後翼間の空力干渉による垂直力について | |||||
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 | An Experimental Study on the Induced Normal Force on Tail-Fins due to Wing-Tail Interference | |||||
著者 |
白水, 正男
× 白水, 正男× 曽我, 国男× 柴藤, 羊二× 秋元, 敏男× SHIROUZU, Masao× SOGA, Kunio× SHIBATO, Yoji× AKIMOTO, Toshio |
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著者所属 | ||||||
航空宇宙技術研究所空気力学第一部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第一部 | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属(英) | ||||||
en | ||||||
First Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
First Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan(NASDA) | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan(NASDA) | ||||||
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-814 巻 814, p. 18, 発行日 1984-05 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The normal force on the tail-fins induced by aerodynamic load on front-fins was studied. The magnitude of the induced normal force was obtained experimentally from a wind tunnel test of two-stage rocket models with both front- and tail-fin, with either front- or tail-fin, and without any fin. The test was performed at M∞ = 0.5 ~ 0.95 and 1.5~2.5, and the induced normal force in this region was about 30%, at maximum, of the normal force which acts on the entire model. The variation of the induced normal force with bank angle difference between front- and tail-fin was also obtained from wind tunnel tests of a roll-controllable rocket model at M∞ = 0.50 ~ 1.20. Those results were compared with predictions based on the strip theory. This simplified theory succeeded in giving approximate magnitude and Mach number dependence of the induced normal force ; however, it is not sufficient for precise prediction. | |||||
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: NALTR0814000 | |||||
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-814 |