Please use this identifier to cite or link to this item: http://hdl.handle.net/11455/68878
標題: Unsteady flow structure and vorticity convection over the airfoil oscillating at high reduced frequency
作者: Kuo, C.H.
Hsieh, J.K.
關鍵字: local circulation;oscillating airfoil;phase-trigger;phase-averaged;technique;constant-rate
Project: Experimental Thermal and Fluid Science
期刊/報告no:: Experimental Thermal and Fluid Science, Volume 24, Issue 3-4, Page(s) 117-129.
摘要: 
Unsteady vortex structures and vorticity convection over the airfoil (NACA 0012), oscillating in the uniform inflow, are studied by flow visualization and velocity measurements. The airfoil, pivoting at one-third of the chord, oscillates periodically near the static stalling angle of attack (AOA) at high reduced-frequency. The phase-triggering and modified phase-averaged techniques are employed to reconstruct the pseudo instantaneous velocity field over the airfoil. During the down stroke cycle, the leading-edge separation vortex is growing and the vortex near the trailing edge begins to shed into the wake. During the upstroke cycle, the leading-edge separation vortex is matured and moves downstream, and the counter clockwise vortex is forming near the trailing edge. Convection speeds and wavelength of the unsteady vortex structure over the airfoil equal to that of the counter clockwise vortex shed into the wake. This kind of vortex structure is termed as "synchronized shedding" type. The wavelength of unsteady vortex structure over the airfoil is significantly different from that at low reduced-frequency. Consistent convection speeds of the leading-edge separation vortex are acquired from the spatial-temporal variations of local circulation and local surface vorticity generation, and equals that predicted from flow visualization. Spatial-temporal variations of the local surface vorticity generation clearly reveal the formation and passage of the leading-edge separation vortex only in the region where the flow does not separate completely from the surface. Significant amounts of the surface vorticity are generated within the leading-edge region of the airfoil during the upstroke cycle. Only negligible amount of surface vorticity is produced within the region of complete flow separation. During the down stroke cycle, the surface vorticity generation is mild along the airfoil surface, except the leading-edge region where a small scale leading-edge separation vortex is forming and growing. (C) 2001 Elsevier Science Inc. All rights reserved.
URI: http://hdl.handle.net/11455/68878
ISSN: 0894-1777
DOI: 10.1016/s0894-1777(01)00044-9
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