| Item type |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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|
タイトル |
Pressure- and Temperature-Sensitive Paint Measurements in Shock Tunnel |
|
言語 |
en |
| 言語 |
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|
言語 |
eng |
| 資源タイプ |
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|
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 |
中村, 佳朗
栗田, 充
Nakamura, Yoshiaki
Kurita, Mitsuru
|
| 著者所属 |
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名古屋大学大学院 工学研究科 航空宇宙工学専攻 |
| 著者所属 |
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名古屋大学大学院 工学研究科 航空宇宙工学専攻 |
| 著者所属（英） |
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|
en |
|
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Department of Aerospace Engineering, Nagoya University |
| 著者所属（英） |
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|
en |
|
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Department of Aerospace Engineering, Nagoya University |
| 出版者 |
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出版者 |
宇宙科学研究所 |
| 出版者（英） |
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出版者 |
Institute of Space and Astronautical Science |
| 書誌情報 |
en : The Institute of Space and Astronautical Science report. S.P. : Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule
巻 17,
p. 191-198,
発行日 2003-03
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| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
Pressure- and temperature-sensitive paint measurements can make possible the measurement of global surface pressure and temperature distributions on a body at a time, which are different from conventional sensors' point measurements. Shock tunnels have been widely used to make hypersonic flows at low cost and to examine the flow field around high-speed vehicles. However, they have a limitation of duration. The present study applies pressure- and temperature-sensitive paints to investigate an interaction flow field due to two bodies, i.e., a hemisphere-cylinder and a delta wing, in a hypersonic flow with M(sub infinity) = 8.1. As a result, the present methods were found to be useful and effective to analyze the hypersonic flow field. |
| ISSN |
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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 |
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|
収録物識別子タイプ |
NCID |
|
収録物識別子 |
AA10455137 |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: SA0200024000 |
SA0200024.pdf (2.0 MB)
