The effects of a forward-sweep angle ( φ ), Reynolds number ( R ), and angle of attack ( α ) 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 2.5 × 10 4 < R < 10 5 and 0 ° φ 45 ° , 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 R , α , and φ : separation, separation bubble, secondary separation, leading-edge bubble, three-dimensional ( φ = 0 ° )/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 ( L b / C ) 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 φ = 30 ° , and α stall of 19.5° at φ = 45 ° was about 1.16-fold larger than that of 9° at φ = 0 ° as R = 8.0 × 10 4 . Namely, the forward-sweep angle retards the stall.


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    Title :

    Boundary-Layer Flow Effects on Aerodynamic Performance of Forward-Swept Wings


    Contributors:
    San, Kuo C. (author) / Fei, Yu F. (author)

    Published in:

    Publication date :

    2011-06-15


    Size :

    92012-01-01 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






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