Surface-Flow Patterns A Swept-Back Wing
Effects of the Reynolds number and angle of attack on the surface flow, the aerodynamic performance, and the vortex shedding of a finite swept-back wing are experimentally studied The cross-sectional profile of the wing is NACA 0012, and the swept-back angle is 15 degrees. The surface flow field is visualized by surface oil-flow techniques. Six characteristic flow regimes, laminar separation, separation bubble, leading-edge bubble, bubble burst, turbulent separation, and bluff-body wake, are studied, with the consideration of Reynolds numbers and the angles of attack. The aerodynamic performances detected by a six component balance show there is no hysteresis phenomenon for the swept-back wing model under the conditions used in this study. With the time series signals detected by hot-wire in the wake region, four significant modes, laminar, subcritical, transitional, and supercritical, can be defined. The derived Strouhal number distributions are significantly distinguished in these four modes. In addition, the statistical properties of turbulence, e. g., the power spectrum density function, probability density function, and correlation coefficient, are also discussed in this paper.
swept-back wing surface oil-flow aerodynamic performances vortex shedding
Shun C.Yen Ching M.Hsu
Department of Mechanical and Mechatronic Engineering, National Taiwan Ocean University Keelung 202,T Department of Mechanical Engineering, National Taiwan University of Science and Technology Taipei 10
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
391-394
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）