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Flow Visualization of Sonic Jets Exhausting Counter to a Supersonic Free Stream Using Laser Induced Fluorescence Method
https://jaxa.repo.nii.ac.jp/records/31335
https://jaxa.repo.nii.ac.jp/records/313356874a546-fcf2-40bd-998a-a563f5e0a979
名前 / ファイル | ライセンス | アクション |
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SA0033608.pdf (945.8 kB)
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Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | Flow Visualization of Sonic Jets Exhausting Counter to a Supersonic Free Stream Using Laser Induced Fluorescence Method | |||||
言語 | en | |||||
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_6501 | |||||
資源タイプ | departmental bulletin paper | |||||
著者 |
TANAKA, Shigeki
× TANAKA, Shigeki× TESHIMA, Koji× UENO, Kazuyuki× NISHIDA, Michio |
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著者所属(英) | ||||||
言語 | en | |||||
値 | Toyobo Research Center, Toboyo Co., Ltd. | |||||
著者所属(英) | ||||||
言語 | en | |||||
値 | Department of Industrial Arts Education, Kyoto University of Education. | |||||
著者所属(英) | ||||||
言語 | en | |||||
値 | Department of Aeronautical Engineering, Kyoto University. | |||||
著者所属(英) | ||||||
言語 | en | |||||
値 | Department of Aeronautical Engineering, Kyoto University. | |||||
出版者 | ||||||
出版者 | 宇宙科学研究所 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science | |||||
書誌情報 |
en : The Institute of Space and Astronautical Science report. S.P. : An Aerodynamics in Relation to an Aeroassisted Orbit Transfer Vehicle 巻 7, p. 73-82, 発行日 1988-11 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The flow field resulting from a sonic nose jet exhausting counter to a supersonic free stream of a Mach number of 3 was visualized by means of a laser induced fluorescence method. The experiments were conducted for various values of the ratio of counter jet total pressure to free-stream total pressure. The ratio of body diameter to jet exit diameter was taken to be 0.2 or 0.4. The results show that the structure of the opposing jets are significantly affected not only by the ratio of jet total pressure to free stream total pressure but also by the ratio of body diameter to jet exit diameter. It was also observed that at the low pressure ratios, there exists unstable flow regime. Simple analysis is applied to the prediction of the position of the free stream shock and Mach disc, and compared with the experimental result. The comparison shows a good agreement. Numerical simulation was also tried to compare with the experiments. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0288-433X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA10455137 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA0033608000 |