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屈曲2重円錐の超音速風洞試験
https://jaxa.repo.nii.ac.jp/records/41190
https://jaxa.repo.nii.ac.jp/records/41190235e764c-5401-45da-84f1-3f092bf1c221
名前 / ファイル | ライセンス | アクション |
---|---|---|
naltr01205.pdf (3.1 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 屈曲2重円錐の超音速風洞試験 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速空気力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速流れ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速風洞 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 鼻曲り2重円錐 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | AOTV | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力制動型軌道間輸送機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙飛行体 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 大迎角試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力分布計測 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | オイルフロー試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 底面圧計測 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 凹面底面圧 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 平面底面圧 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ニュートン流近似 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic aerodynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic wind tunnel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | bent nose biconic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | AOTV | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Aeroassisted Orbital Transfer Vehicle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | space vehicle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | large angle of attack test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure distribution measurement | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | oil flow test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | base pressure measurement | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | concave base base pressure | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flat base base pressure | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Newtonian flow approximation | |||||
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 | Investigation of experimental bent-nose biconic design in supersonic flow | |||||
著者 |
関根, 英夫
× 関根, 英夫× 野田, 順一× 石田, 清道× 谷, 喬× Sekine, Hideo× Noda, Junichi× Ishida, Kiyomichi× Tani, Takashi |
|||||
著者所属 | ||||||
航空宇宙技術研究所 空気力学部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 空気力学部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 空気力学部 | ||||||
著者所属 | ||||||
東京農工大学 工学部 機械システム工学科 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo University of Agriculture and Technology Department of Mechanical Systems Engineering, Faculty of Technology | ||||||
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 巻 1205, p. 1-20, 発行日 1993-05 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | AOTV(空力制動型軌道間輸送機)の1形態である屈曲2重円錐の超音速風洞実験結果を示す。超高速飛行体についても低超音速域空力性能試験の必要が考えられる。本試験は特に大迎角試験、表面の流れの剥離測定、底面圧計測および簡単な理論推定法のチェックなどに重点がおかれた。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Preliminary wind tunnel tests of a Bent-Nose Biconic were conducted in the NAL 1m X 1m blow-down supersonic wind tunnel to evaluate its aerodynamics in the moderate supersonic range. Aerodynamic data at attack angles of up to 50 deg was obtained for a 30 deg bent-sting. A flow-separated zone on the rear side of the body was observed by surface pressure distribution and oil-flow tests. Estimates based on Newtonian flow theory were not accurate when the attack angle was small for this rather slender configuration. | |||||
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: AA0004220000 | |||||
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-1205 |