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title低Re数でのNACA0012翼上に見られる層流剥離・剥離泡を伴う流れ場
Other TitleFlow Field Phenomena Contains Laminar Separation and Separation Bubble on NACA0012 Airfoil at Low Reynolds Numbers
Author(jpn)大竹, 智久; 中江, 雄亮; 村松, 旦典; 本橋, 龍郎
Author(eng)Otake, Tomohisa; Nakae, Yusuke; Muramatsu, Akinori; Motohashi, Tatsuo
Author Affiliation(jpn)日本大学理工学部; トヨタ自動車; 日本大学理工学部; 日本大学理工学部
Author Affiliation(eng)College of Science and Technology, Nihon University; TOYOTA MOTOR; College of Science and Technology, Nihon University; College of Science and Technology, Nihon University
Issue Date2011-02-28
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication titleJAXA special publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010
宇宙航空研究開発機構特別資料: 第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 論文集
VolumeJAXA-SP-10-012
Publication date2011-02-28
Languagejpn
eng
AbstractWe carried out flow measurements using a CTA hot-wire anemometer to clarify flow field phenomena contains laminar separation and separation bubble on NACA0012 airfoil at three low Reynolds numbers; Re = 10,000, 30,000 and 50,000. A laminar separation region was observed on the airfoil near the trailing edge when the angle of attack was nearly 0.0 deg. at all Reynolds numbers. The instability of the laminar separation region induced the growth of turbulent intensity in the separated shear layer on the airfoil. The growth of turbulent intensity caused a reattachment of the separated boundary layer on the airfoil surface, and a separation bubble formed on the airfoil. The separation bubble observed over a rather wide range of angle of attack until the maximum lift coefficient was reached at Re = 30,000 and 50,000. However, the separation bubble was also observed in the narrow range of angle of attack of from 7.0 deg. to 8.0 deg. at Re = 10,000. The flow field phenomena on the airfoil at Re = 10,000 shows that the laminar separation region extended with the movement of the separation point, and the separated shear layer was detached from the airfoil surface until the maximum lift coefficient was reached. This difference of flow field phenomena on the airfoil, the changing process of flow pattern from laminar separation region to separation bubble depended on the Reynolds numbers, might play an essential role in the performance of the airfoil at low Reynolds numbers consequently.
DescriptionOriginal contains color illustrations
Meeting Information: 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25, 2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan
形態: カラー図版あり
会議情報: 第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP)
Document TypeConference Paper
JAXA Category特別資料
ISSN1349-113X
NCIDAA11984031
SHI-NOAA0064967049
Report NoJAXA-SP-10-012
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/14923


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