![]() In a smoke tunnel, the streamlines can be visualized as smoke lines. The technique estimating the sectional lift coefficient from the flow visualization results in the 2D smoke tunnel was proposed by Yamana, and it was successfully applied to the basic airfoil and the cases of flaps. Several experimental investigations on estimating the lift coefficient of airfoils in two-dimensional (2D) smoke tunnels have been performed. The installation of a GF with a height equal to 1% of the chord length of the airfoil significantly improved the low-speed aerodynamic performance of SC airfoils. ![]() When the height of the flap was increased, the lift and drag coefficients increased. In the case of flaps, the GFs have an observable effect on the aerodynamic performance of the SC-0414 airfoil. However, the slope of the lifts calculated from y s is higher and closer to the reference data than those obtained from s c, where y s denotes the height where the distance from the streamline to the reference line is the largest, and s c denotes the displacement of the center of pressure from the origin of the coordinate, respectively. In clean condition, the lift coefficients calculated from the two methods show quantitative agreement, and no significant difference could be confirmed. As a result, the estimated lift coefficients show a good agreement with the results from reference data and numerical simulations. The flow velocity was 12 m/s and the Reynolds number was 1.6 × 10 5. ![]() The angle of attack was varied from −5 ° to 8 °. Additionally, the lift estimation, wake measurements, and numerical simulations are performed to clarify the low-speed aerodynamic characteristics of the SC airfoil with flaps. The application of the modified Yamana’s method is evaluated with two calculation methods. In this paper, the lift coefficients of SC-0414 airfoil are estimated by applying modified Yamana’s method to the flow visualization results, which are obtained by utilizing the smoke tunnel. ![]()
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