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|Title: ||Aerodynamic Performance and Shedding Characteristics on a Swept-Back Wing.|
|Authors: ||Shun-Chang Yen|
|Contributors: ||NTOU:Department of Mechanical and Mechatronic Engineering|
|Keywords: ||swept-back wing;vortex shedding;aerodynamic coefficients|
|Issue Date: ||2011-10-20T08:09:30Z
|Publisher: ||Journal of Marine Science and Technology|
|Abstract: ||Abstract:A NACA 0012 finite swept-back wing with a sweep-back angle of 15° was utilized to investigate the effects of angle of attack (α) and the chord Reynolds number (Rec) on the vortex shedding and aerodynamic coefficients. A hot-wire anemometer was applied to measure the vortex-shedding frequency. The projected Strouhal number (Std) at various angles of attack was determined and discussed. The relationship between Std and α is regressed as: Std = -0.0008α + 0.209, for 22° < α < 90°. Four characteristic surface-flow patterns: separation bubble, leading-edge bubble, bubble burst, and turbulent separation were classified by changing α and Re. The behavior of surface-flow structures significantly affects the lift, drag, and moment coefficients. The lift coefficient (CL)
increases with α in the separation bubble and leading-edge bubble regimes. The maximum increase rate of CL with respect to α (d(CL)/dα) is 1.52 π/rad. Occurring in the leading- edge bubble regime. However, the maximum increase rate of drag coefficient (C
D) with respect to α (d(CD)/dα) is 0.49 π/rad. Occurring in the bubble-burst regime. The steep-drop of moment coefficient at stall in the unswept-wings is not observed in the swept-back wings.
|Relation: ||19(2), pp.162-167|
|Appears in Collections:||[機械與機電工程學系] 期刊論文|
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