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Please use this identifier to cite or link to this item: http://ntour.ntou.edu.tw:8080/ir/handle/987654321/23810

Title: Flow Patterns and Aerodynamic Performance of Unswept and Swept-Back Wings
Authors: YEN Shun C;HUANG Lung―C.
閻順昌
Contributors: NTOU:Department of Mechanical and Mechatronic Engineering
國立臺灣海洋大學:機械與機電工程學系
Keywords: Swept-back wings;Surface oil-flow;Aerodynamic performance
Date: 2009
Issue Date: 2011-10-20T08:08:20Z
Publisher: American Society of Mechanical Engineers
Abstract: Abstract:The effects of sweep-back angle (Λ), Reynolds number (Re), and angle of attack (α) on the boundary-layer flow structures and aerodynamic performance of a finite swept-back wing were experimentally investigated. The Reynolds number and sweep-back angle used in this test is 30,000<Re<130,000 and 0 deg≤Λ≤45 deg. The wing model was made of stainless steel, and the wing airfoil is NACA 0012. The chord length is 6 cm, and the semiwing span is 30 cm; and therefore, the semiwing aspect ratio is 5. The boundary-layer flow structures were visualized using the surface oil-flow technique. Seven boundary-layer flow modes were categorized by changing Re and α. A six-component balance is used to determine aerodynamic loadings. The aerodynamic performance is closely related to the boundary-layer flow modes. The stall angle of attack (αstall) is deferred from 9 deg to 10 deg (for an unswept wing), to 30 deg to 35 deg (for a swept-back wings of A > 30 deg). The deferment of αstall is induced from the increased rotation energy and turbulent intensity generated from the secondary flow. Furthermore, the increased rotation energy and turbulent intensity resisted the reverse pressure generated at high α.
Relation: 131(11)
URI: http://ntour.ntou.edu.tw/handle/987654321/23810
Appears in Collections:[機械與機電工程學系] 期刊論文

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