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マッハ2における小型超音速実験機の遷移特性
https://jaxa.repo.nii.ac.jp/records/38100
https://jaxa.repo.nii.ac.jp/records/38100268896d2-679a-4869-9f01-b228a3278688
名前 / ファイル | ライセンス | アクション |
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nalsp0054008.pdf (1.9 MB)
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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 | マッハ2における小型超音速実験機の遷移特性 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速実験機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 遷移特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱フィルム風速計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 赤外カメラ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 横流れ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 風洞 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic experimental airplane | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | transition characteristic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hot film anemometer | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | infrared camera | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure distribution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | cross flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wind tunnel | |||||
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 | Transition characteristics of non-powered experimental airplane at Mach 2 | |||||
著者 |
杉浦, 裕樹
× 杉浦, 裕樹× 高木, 正平× 徳川, 直子× 西沢, 啓× Sugiura, Hiroki× Takagi, Shohei× Tokugawa, Naoko× Nishizawa, Akira |
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著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
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: 第28回境界層遷移の解明と制御研究会講演論文集 en : Special Publication of National Aerospace Laboratory: Proceedings of the 28th NAL Workshops on Investigation and Control of Boundary-Layer Transition 巻 54, p. 27-30, 発行日 2002-01 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Transition on the natural laminar flow wing of a non-powered scaled supersonic experimental airplane was measured by hot-film sensors and an infrared camera at Mach 2. In order to supress crossflow instability which dominates the transition on the highly swept wing, the pressure falls very rapidly in the vicinity of leading edge of the wing, so as to minimize the crossflow velocity components. The unit Reynolds number had no effect on the transition Reynolds numbers of the wing. The transition Reynolds number was 0.8 million at 70 percent semi-spanwise location at Mach 2 at the angle of attack of 2 deg. Transition location in flight was estimated by conducting transition measurement in a quiet low Reynolds number wind tunnel and in a variable unit Reynolds number wind tunnel which has moderately low turbulence. The transition at 70 percent semi-spanwise position at the angle of attack of 2 deg at Mach 2 in flight was predicted to be located downstream of 60 percent chordwise position. | |||||
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: AA0032827008 | |||||
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-54 |