@inproceedings{oai:jaxa.repo.nii.ac.jp:00006529,
 author = {中北, 和之 and 栗田, 充 and 満尾, 和徳 and 神田, 宏 and 渡辺, 重哉 and 浅井, 圭介 and Nakakita, Kazuyuki and Kurita, Mitsuru and Mitsuo, Kazunori and Kanda, Hiroshi and Watanabe, Shigeya and Asai, Keisuke},
 book = {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, JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 69th Meeting},
 month = {Feb},
 note = {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., 資料番号: AA0048061004, レポート番号: JAXA-SP-04-008},
 pages = {17--21},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {NAL1m×1m超音速風洞におけるSST模型感圧塗料試験},
 volume = {JAXA-SP-04-008},
 year = {2005}
}