Experimental and Numerical Investigations of Flow over a Pitching Airfoil in Periodic Flow
デジタルデータあり（科学技術振興機構）
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- 資料種別
- 記事
- 著者・編者
- Yoshitaka ISODAYohsuke TANAKATakuma SADANAGAShigeru MURATA
- タイトル（掲載誌）
- Advanced experimental mechanics / Editorial board for advanced experimental mechanics [編]
- 巻号年月日等（掲載誌）
- 6:2021.8
- 掲載巻
- 6
- 掲載ページ
- 27-32
- 掲載年月日（W3CDTF）
- 2021-08
- ISSN（掲載誌）
- 2189-4752
- ISSN-L（掲載誌）
- 2189-4752
- 出版事項（掲載誌）
- Niigata : The Japanese Society for Experimental Mechanics
- 出版地（国名コード）
- JP
- 本文の言語コード
- eng
- NDLC
- 対象利用者
- 一般
- 所蔵機関
- 国立国会図書館
- 請求記号
- Z63-D560
- 連携機関・データベース
- 国立国会図書館 : 国立国会図書館雑誌記事索引
- 書誌ID（NDLBibID）
- 031655614
- 整理区分コード
- 632
- 要約等
- <p>The purpose of this study is to investigate the influence of periodic flow on the laminar boundary layer of a pitching NACA 0012 airfoil at a low Reynolds number. The periodic flow is the freestream oscillating sinusoidally in the streamwise direction. The velocity field is measured by particle image velocimetry (PIV) under the conditions of a Reynolds number of 3700 and a reduced frequency of 2.01. In the processing, we introduce an overlapping technique and a rectangular interrogation window to evaluate the boundary layer profile with high spatial resolution. However, the velocity on the airfoil surface cannot be obtained because of the angle of view, so a numerical simulation is performed under the same conditions to obtain the velocity data on the surface. The flow reversal related to dynamic stall is evaluated with the wall shear stress calculated by numerical simulation, which is confirmed to agree with the boundary layer profile obtained by PIV. The periodic flow case is compared with the steady case to determine the effect of freestream oscillation on the flow reversal. It is found that the reversed flow vanishes during freestream acceleration, whereas the reversed flow region increases during freestream deceleration.</p>
- DOI
- 10.11395/aem.6.0_27
- オンライン閲覧公開範囲
- インターネット公開
- 連携機関・データベース
- 科学技術振興機構 : J-STAGE
- 要約等
- <p>The purpose of this study is to investigate the influence of periodic flow on the laminar boundary layer of a pitching NACA 0012 airfoil at a low Reynolds number. The periodic flow is the freestream oscillating sinusoidally in the streamwise direction. The velocity field is measured by particle image velocimetry (PIV) under the conditions of a Reynolds number of 3700 and a reduced frequency of 2.01. In the processing, we introduce an overlapping technique and a rectangular interrogation window to evaluate the boundary layer profile with high spatial resolution. However, the velocity on the airfoil surface cannot be obtained because of the angle of view, so a numerical simulation is performed under the same conditions to obtain the velocity data on the surface. The flow reversal related to dynamic stall is evaluated with the wall shear stress calculated by numerical simulation, which is confirmed to agree with the boundary layer profile obtained by PIV. The periodic flow case is compared with the steady case to determine the effect of freestream oscillation on the flow reversal. It is found that the reversed flow vanishes during freestream acceleration, whereas the reversed flow region increases during freestream deceleration.</p>
- DOI
- 10.11395/aem.6.0_27
- 参照
- Scaling and lateral maneuverability of pitching foil in periodic freestream
- 連携機関・データベース
- 国立情報学研究所 : CiNii Research
- 提供元機関・データベース
- Japan Link Center雑誌記事索引データベースCiNii ArticlesCrossref
- 書誌ID（NDLBibID）
- 031655614
- NII論文ID
- 130008127473