タイトル(別表記) Fast-framing Focusing Schlieren Visualization of Two-dimensional Wing Buffet
フルテキストURL TransJSASS_63_4_166.pdf
著者 河内 俊憲| 山口 真伍| 小池 俊輔| 中島 努| 佐藤 衛| 神田 宏| 柳瀬 眞一郎|
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 10.2322/jjsass.63.166
関連URL isVersionOf https://doi.org/10.2322/jjsass.63.166