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Numerical Study on Anomalous Heating over Apollo CM Test Model in Free-Piston Shock Tunnel HIEST
https://jaxa.repo.nii.ac.jp/records/4134
https://jaxa.repo.nii.ac.jp/records/4134056cc09e-a07c-47f7-9e34-71ab14d0a4fd
名前 / ファイル | ライセンス | アクション |
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62070026.pdf (997.4 kB)
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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 | ||||||
言語 | en | |||||
タイトル | Numerical Study on Anomalous Heating over Apollo CM Test Model in Free-Piston Shock Tunnel HIEST | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hypersonic flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic heating | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | shock 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 | |||||
著者 |
石原, 知明
× 石原, 知明× 荻野, 要介× 大西, 直文× 澤田, 恵介× 丹野, 英幸× Ishihara, Tomoaki× Ogino, Yousuke× Ohnish, Naofumi× Sawada, Keisuke× Tanno, Hideyuki |
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著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構角田宇宙センター(JAXA)(KSPC) | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Space Center, Japan Aerospace Exploration Agency (JAXA)(KSPC) | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構(JAXA) | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料 en : JAXA Special Publication 巻 JAXA-SP-13-001E, p. 317-325, 発行日 2013-11-30 |
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会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 5th Symposium on Integrating CFD and Experiments in Aerodynamics (October 3-5, 2012, Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)), Chofu, Tokyo, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Aeroheating measurements on the Apollo CM test model placed in the free-piston shock tunnel HIEST was conducted. Although the convective heat flux distributions along wall surface normalized by a product of Stanton number and the square root of the Reynolds number should fall on a single curve for laminar flow case, the measured data for high enthalpy conditions resulted in significantly larger than one for low enthalpy conditions. In the HIEST experiment, stagnation heat fluxes on small probes were also measured. We could find that the anomalous heating phenomena are not shown for small test model but for large one that is called the scaling effect of anomalous heating phenomena. Similar tendencies were also observed at other shock tunnels: NASA Ames 42-Inch Shock Tunnel, Caltec T5, and CUBRC LENS. The cause for those anomalous heating phenomena is yet unknown. Anomalous heating poses a critical issue over the existing design method of thermal protection system for entry capsules. To clarify the cause of it, we numerically investigate these two factors: The radiative heat transfer in the shock layer and the radiation heating from the driver gas. From the results of our computations, radiative heating from shock layer was negligibly small. While, obtained total heat flux considering radiative heating from driver gas agreed well with measured heat flux. Scaling effect of the anomalous heating phenomena was also explained by accounting for the radiation from the driver gas. Therefore, we can say that the radiative heating from the driver gas may be the cause of those phenomena. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0062070026 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-13-001E |