Visualization Study of Flow Near the Trailing Edge of an Oscillating Airfoil
スポンサーリンク
概要
- 論文の詳細を見る
For the calculation of unsteady flow around an airfoil, the following assumptions are usually made: 1) Wake is straight, 2) Shed vorticities move downstream with uniform velocity, 3) Kutta-Joukowski's condition holds at the trailing edge. To estimate the validity of these assumptions, wake pattern of a translatorily oscillating airfoil in a uniform flow was visualized by Schlieren method. Instantaneous wake patterns were photographed at reduced frequency between 1 and 19. Observed wake patterns were classified into three types. The range of reduced frequency and oscillation amplitude for each type was given. Kutta-Joukowski's condition was found to be valid at any test condition in the sense that a dividing stream line detached the airfoil at the trailing edge.
- 一般社団法人日本機械学会の論文
著者
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Ohashi Hideo
Faculty Of Agriculture Gifu University
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ISHIKAWA Norikatsu
Higashifuii Technical Center, Toyota Motor Co., Ltd,
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Ishikawa Norikatsu
Higashifuii Technical Center Toyota Motor Co. Ltd
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- Visualization Study of Flow Near the Trailing Edge of an Oscillating Airfoil