National Aerospace Laboratory Wind Tunnel Technology Center
National Aerospace Laboratory Wind Tunnel Technology Center
National Aerospace Laboratory Wind Tunnel Technology Center
National Aerospace Laboratory Wind Tunnel Technology Center
National Aerospace Laboratory Wind Tunnel Technology Center
National Aerospace Laboratory Wind Tunnel Technology Center
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料: 第66回 風洞研究会議論文集
雑誌名(英)
JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 66th Meeting
巻
JAXA-SP-03-003
ページ
13 - 22
発行年
2004-03-25
抄録（英）
The Mach 10 nozzle of the National Aerospace Laboratory phi1.27 m hypersonic wind tunnel was calibrated at lower total temperature conditions which gave reduction of thermal load of the facility and the lowest total pressure (P0 = 1.0 MPa) operation. Repeatability among multi point calibration tests and non-liquefied flow were examined by statistical uncertainty assessment of measured Mach numbers. Enlargement of the Re number range, reduction of total temperature about 100 K and heat up time of the air heater were successfully attained. Represented statistical uncertainties of flow conditions clearly show that the NAL 1.27 m tunnel has better flow uniformity than that of the AEDC VKF-C tunnel.
1.27m極超音速風洞の通風領域拡大:不確かさの表記と応用
47428003.pdf
(1.22MB)
