Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
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72回風洞研究会議論文集
雑誌名(英)
JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 72nd Meeting
巻
JAXA-SP-04-013
ページ
14 - 20
発行年
2005-03-30
抄録（英）
A series of wind tunnel tests were conducted to develop a boundary-layer tripping technique and also a detection technique for the boundary-layer state in transonic wind tunnels in ISTA/JAXA. A commonly used disk-type roughness element was used in the test and the conventional criterion for the effective roughness height was confirmed valid in the present case, also. A detection methodology for the boundary-layer state based on the quantitative measurement of the aerodynamic heating was applied to this experiment in a blow-down transonic facility, using both the Temperature Sensitive Paint (TSP) technique and the Infra-Red Thermograpy (IR) technique. The results indicate the methods are both useful in transonic experiments. Transition detection in a closed-circuit transonic wind tunnel was also achieved by varying the reservoir temperature, but it is found that the technique is not necessarily good for the boundary-layer state determination without any additional roughness for the reference purpose.
WINTECにおける境界層遷移位置計測法整備へ向けた遷音速試験
48470003.pdf
(2.41MB)
