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Due to the consideration of less angle of attack in the Airfoil, the previous studies didn’t achieve accurate results on velocity and pressure of air fluid. Also, previous studies haven’t taken into a...ccount both the coefficients of drag and lift forces at the same time. In this study, first-time we used the NACA 4412 (national advisory committee for aeronautics 4412) Airfoil because of its availability, lightweight, and flat bottom surface which prevents negative ground effects. Here the NACA 4412 Airfoil surface characteristics were studied through ANSYS Fluent laminar flow analysis as well as pressure-based ANSYS fluent solver. When we increased the angle of attack from 0º to 18º the coefficients of lift and drag forces increase gradually, which impacts the values of the velocity of the upper surface and pressure of the lower surface in the air-fluid. The coefficient of lift and drag forces on the airfoil's surface were 0.44 and 0.5, while the velocity and pressure at the surface are 80.5354 ms^-1and 2.12 × 10^3 Pa respectively at a 16º angle.続きを見る
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Mendeley出力
