2017 Cilt 22 Sayı 1

Permanent URI for this collectionhttps://hdl.handle.net/11452/11961

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Browsing by Subject "Airfoil simulation"

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    Numerical simulation of 4-digit inclined NACA 00xx airfoils to find optimum angle of attack for airplane wing
    (Uludağ Üniversitesi, 2017-02-28) Sogukpinar, Haci
    In this paper, numerical analysis was conducted by using the SST turbulence model for inclined NACA 0008, 0009, 0010, 0012, 0015, 0018, 0021, 0024 airfoils. Aerodynamic numerical analysis of NACA 0012 airfoil was compared with the previously made experimental results in terms of pressure and lift coefficient. The theoretical data were found to be fully compatible with experimental results. Then, by simulating other airfoils using the same methods lift, drag, lift to drag ratio and the pressure coefficient were calculated and compared with the angle of attack 0-14 degrees. According to the calculations, lift coefficient of NACA 0008-0012 airfoil shows similar behaviors. With the increasing of the airfoil thickness increment in the lift coefficient decreases for NACA 0015-0024 airfoils. Pressure coefficients were also calculated for NACA profiles with angle of attack 10°. Pressure coefficients over the airfoil decrease from leading edge toward the trailing edge but in the lower part it increases. With the increasing of the airfoil thickness pressure coefficient decreases more slowly at the upper part but increases more rapidly at the lower.