The effects of the Reynolds number and angle of attack on the boundary layer and the aerodynamic performance of a finite swept-back wing are studied experimentally. The cross-sectional profile of the wing is NACA 0012 (aspect ratio=10), and the sweep-back angle is 15 deg. The Reynolds number is set in the range of 30,000–130,000. The boundary layer field is visualized with surface oil-flow techniques. Six characteristic flow regimes—laminar separation, separation bubble, leading-edge bubble, bubble burst, turbulent separation, and bluff-body wake—are categorized and studied by considering the Reynolds numbers and angles of attack. The characteristic behaviors of boundary layer significantly affect the lift, drag, and moment coefficients. The bubble length shortens significantly in the separation bubble and leading-edge bubble regimes as the angle of attack rises. The aerodynamic performances demonstrate that the swept-back wing model has no hysteresis.
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e-mail: scyen@mail.ntou.edu.tw
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June 2007
Technical Papers
Influence of Boundary Layer Behavior on Aerodynamic Coefficients of a Swept-Back Wing
S. C. Yen,
S. C. Yen
Assistant Professor
Department of Mechanical and Mechatronic Engineering,
e-mail: scyen@mail.ntou.edu.tw
National Taiwan Ocean University
, No. 2, Pei-Ning Road, Keelung, Taiwan 202, Republic of China
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C. M. Hsu
C. M. Hsu
Department of Mechanical Engineering,
National Taiwan University of Science and Technology
, Taipei, Taiwan 106, Republic of China
Search for other works by this author on:
S. C. Yen
Assistant Professor
Department of Mechanical and Mechatronic Engineering,
National Taiwan Ocean University
, No. 2, Pei-Ning Road, Keelung, Taiwan 202, Republic of Chinae-mail: scyen@mail.ntou.edu.tw
C. M. Hsu
Department of Mechanical Engineering,
National Taiwan University of Science and Technology
, Taipei, Taiwan 106, Republic of ChinaJ. Fluids Eng. Jun 2007, 129(6): 674-681 (8 pages)
Published Online: December 18, 2006
Article history
Received:
February 10, 2006
Revised:
December 18, 2006
Citation
Yen, S. C., and Hsu, C. M. (December 18, 2006). "Influence of Boundary Layer Behavior on Aerodynamic Coefficients of a Swept-Back Wing." ASME. J. Fluids Eng. June 2007; 129(6): 674–681. https://doi.org/10.1115/1.2734212
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