ライブラリ登録: Guest
TSFP DL Home アーカイブ 執行委員会
TSFP DIGITAL LIBRARY ONLINE


ISSN オンライン: 2642-0554

INFLUENCE OF ANGLE OF ATTACK ON SYNTHETIC JET EFFECTIVENESS AS FOUND WITH COEFFICIENT OF MOMENTUM

Mark A. Feero
Institute for Aerospace Studies University of Toronto 4925 Dufferin Street, Toronto, ON, Canada M3H 5T6

Sebastian D. Goodfellow
Department of Mechanical and Industrial Engineering University of Toronto 5 King's College Road, Toronto, ON, Canada M5S 3G8

Philippe Lavoie
Department of Aerospace Studies University of Toronto 4925 Dufferin Street Toronto, Ontario, Canada M3H 5T6

Pierre E. Sullivan
Mechanical and Industrial Eng. University of Toronto Toronto, Ontario, M5S 3G8, Canada

要約

The influence of periodic excitation from a synthetic jet actuator on the flow separation over a NACA 0025 airfoil at an angle of attack of 10° was investigated. Experiments were performed in a low-speed wind tunnel at a chord-based Reynolds number Rec = 105. At Rec = 105, the boundary layer separates and fails to reattach at angles of attack from 0 − 10°. When the boundary layer was forced at a momentum coefficient Cµ = 2.47 × 10−2 and excitation frequency fe = 970 Hz, the vortex shedding associated with the uncontrolled case was eliminated and the drag coefficient was reduced by 22%. These results were compared to previous work at α = 5° on the same airfoil by Goodfellow et al. (2012), who found that a drag reduction of 52% was achieved at Cµ = 3.09 × 10−3. The results suggest that as the angle of attack is increased from 5° to 10°, the synthetic jet actuator must transfer more momentum to the separated boundary layer in order to cause drag reduction.