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Visualization of Hypersonic Boundary Layer Transition on Elliptic Cone in High Enthalpy Shock Tunnel with Temperature-Sensitive Paint
https://jaxa.repo.nii.ac.jp/records/38833
https://jaxa.repo.nii.ac.jp/records/38833547af2a5-50d0-429c-af59-933146976c95
Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2016-09-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Visualization of Hypersonic Boundary Layer Transition on Elliptic Cone in High Enthalpy Shock Tunnel with Temperature-Sensitive Paint | |||||
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_5794 | |||||
資源タイプ | conference paper | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
著者 |
長山, 武広
× 長山, 武広× 永井, 大樹× 丹野, 英幸× 小室, 智幸× Nagayama, Takehiro× Nagai, Hiroki× Tanno, Hideyuki× Komuro, Tomoyuki |
|||||
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(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
出版者(英) | ||||||
出版者 | American Institute of Aeronautics and Astronautics(AIAA) | |||||
書誌情報 |
en : 54th AIAA Aerospace Sciences Meeting, AIAA SciTech 発行日 2016-01 |
|||||
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 | 54th AIAA Aerospace Sciences Meeting (January 4-8, 2016.) San Diego, California, USA | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A flow visualization with TSP (Temperature-sensitive paint) was given on the hypersonic boundary layer transition on an elliptic cone in the High Enthalpy Shock Tunnel JAXAHIEST. The present study firstly investigated the issue of white basecoat thickness to the luminescent intensity and temperature sensitivity of TSP, which was particularly produced for short duration measurements. It was discovered that the thickness of basecoat does not touch on the characteristic of TSP. Moreover, thickness of 15 micro-m was found to raise the maximum luminescent intensity of TSP. With the basecoat and the TSP, surface temperature successfully visualized the hypersonic boundary layer transition on a side of the cone at stagnation enthalpy H0 = 3.0 MJ/kg. Accuracy of the present measurement was discussed through the comparison with thermocouple measurements involving surface temperature augmentation due to boundary layer transition. | |||||
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 | |||||
ISBN | ||||||
識別子タイプ | ISBN | |||||
関連識別子 | 978-1-62410-393-3 | |||||
DOI | ||||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.2514/6.2016-0358 | |||||
関連名称 | info:doi/10.2514/6.2016-0358 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AC1600103000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: AIAA 2016-0358 |