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NAL1m×1m超音速風洞におけるSST模型感圧塗料試験
https://jaxa.repo.nii.ac.jp/records/6529
https://jaxa.repo.nii.ac.jp/records/652970d5941e-d350-4707-ad85-aad97b08bcb3
名前 / ファイル | ライセンス | アクション |
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48061004.pdf (1.8 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 | NAL1m×1m超音速風洞におけるSST模型感圧塗料試験 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | SST模型 | |||||
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 | PSP | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙機配置 | |||||
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 | 圧力センサ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CCDカメラ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CFD | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | SST model | |||||
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 | PSP | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | spacecraft configuration | |||||
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 | pressure sensor | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CCD camera | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD | |||||
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 | Pressure-sensitive paint test using a SST configuration model at the NAL 1 m x 1 m supersonic wind tunnel | |||||
著者 |
中北, 和之
× 中北, 和之× 栗田, 充× 満尾, 和徳× 神田, 宏× 渡辺, 重哉× 浅井, 圭介× Nakakita, Kazuyuki× Kurita, Mitsuru× Mitsuo, Kazunori× Kanda, Hiroshi× Watanabe, Shigeya× Asai, Keisuke |
|||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
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: 第69回風洞研究会議論文集 en : JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 69th Meeting 巻 JAXA-SP-04-008, p. 17-21, 発行日 2005-02-28 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Pressure-sensitive paint techniques make the measurement of global surface pressure distributions possible, which are different from point measurements by conventional pressure transducers. The present study was conducted to make the pressure-sensitive paint measurement practicable at the NAL 1 m x 1 m supersonic wind tunnel. Since the temperature of a model decreases with test time in the wind tunnel, the temperature dependence of luminescent intensity of the pressure-sensitive paint is a large source of error for pressure measurements. A temperature-correction method using a temperature-sensitive paint for the pressure-sensitive paint was applied. The temperature-corrected pressure-sensitive paint data were compared with pressure data using pressure transducers. As a result, good agreements were obtained between the pressure-sensitive paint data and pressure transducer data. | |||||
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: AA0048061004 | |||||
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-04-008 |