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ID 56129
タイトル(別表記)
Fast-framing Focusing Schlieren Visualization of Two-dimensional Wing Buffet
フルテキストURL
著者
河内 俊憲 岡山大学大学院自然科学研究科
山口 真伍 岡山大学大学院自然科学研究科
小池 俊輔 宇宙航空研究開発機構
中島 努 宇宙航空研究開発機構
佐藤 衛 宇宙航空研究開発機構
神田 宏 宇宙航空研究開発機構
柳瀬 眞一郎 岡山大学大学院自然科学研究科
抄録
We visualized two-dimensional wing buffet using fast-framing focusing schlieren method. A supercritical airfoil of NASA SC(2)-0518 was used in this study. Mach number of the freestream was 0.7, and Reynolds number based on the wing code (c) was 5×106. Angle of attack without corrections (α) was changed from 4° to 6°. The present focusing schlieren system had ±18mm depth of field, which was narrow than spanwise region where the two-dimensionality of the flow field was maintained. 8,345 successive images were captured by high speed CMOS camera with 7,000 frames per second with 20μs exposure time. The present imaging system well captured the shock wave motion on the airfoil. At α = 4°, the shock wave was positioned at x/c∼0.45. The shock wave was slightly fluctuated with a frequency of 585.5Hz. Above α = 5°, the wing buffet occurred. The buffet frequency increased as increasing α. The focusing schlieren movies revealed that the shock wave was bifurcated on the wing surface, as the shock traveling upstream. The boundary layer largely separated from the leading oblique foot of the bifurcated shock wave, whereas, the bifurcated shock wave changed into a normal shock and the flow separation disappeared, as the shock traveling downstream. For both cases, many pressure waves propagated from the downstream of the shock wave to the upstream. These waves merged with the shock wave, and seem to drive the shock oscillation.
キーワード
Flow Visualization
Shock-boundary Layer Interaction
Supercritical Airfoil
Two-dimensional Transonic Wind tunnel
発行日
2015-07-28
出版物タイトル
日本航空宇宙学会論文集
63巻
4号
出版者
日本航空宇宙学会
開始ページ
166
終了ページ
174
ISSN
13446460
NCID
AA11307372
資料タイプ
学術雑誌論文
言語
Japanese
OAI-PMH Set
岡山大学
論文のバージョン
publisher
DOI
関連URL
isVersionOf https://doi.org/10.2322/jjsass.63.166