The effects of a forward-sweep angle (), Reynolds number (), and angle of attack () on the boundary-layer flow and aerodynamic performance of a finite forward-swept wing (NACA 0012 airfoil) were experimentally investigated. The Reynolds number and the forward-sweep angle were and , respectively. The chord length was 6 cm, and the semiwing span was 30 cm; therefore, the semiwing aspect ratio was 5. The boundary-layer flow structures were visualized using the surface-oil-flow technique. Seven boundary-layer flow modes were identified by changing , , and : separation, separation bubble, secondary separation, leading-edge bubble, three-dimensional ()/bubble-extension flow, and bluff-body wake modes. Furthermore, a six-component balance measured the aerodynamic loadings. The aerodynamic performance related closely to the boundary-layer flow modes. The dimensionless bubble length () indicated that a high forward-sweep angle conducted a longer bubble length than that at a low forward-sweep angle. The pseudostall occurred in the bubble-extension mode, while , and of 19.5° at was about 1.16-fold larger than that of 9° at as . Namely, the forward-sweep angle retards the stall.
Boundary-Layer Flow Effects on Aerodynamic Performance of Forward-Swept Wings
Journal of Aerospace Engineering ; 25 , 4 ; 627-635
15.06.2011
92012-01-01 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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