Numerical Investigation of Straight-Slot Angle and Width Effects on the Aerodynamic Performance of a NACA ۰۰۱۲ Airfoil

The purpose of optimizing airfoil performance is to enhance the efficiency of airfoils by reducing the drag force and increasing the lift-to-drag ratio, while also decreasing the cost and complexity of the design for various aerodynamic applications. This study numerically investigates the effects of straight-slot angle and width on the aerodynamic performance of a NACA ۰۰۱۲ airfoil. ۶ modified configurations were simulated using ANSYS Workbench. The results illustrated that original NACA۰۰۱۲ airfoil generally exhibits superior overall efficiency compared to the modified versions, the modified geometries show enhanced performance at high angles of attack (AoAs). Four slot angles of ۲۸°, ۶۰°, ۹۰° and ۱۳۰° along with two slot widths, were examined over different angles of attack. The results show that slot effectiveness strongly depends on the operating condition. The ۹۰° configuration achieved the highest CL/CD at ۵°, while the ۲۸° slot performed better at ۱۰° and ۱۵°. Increasing the slot width generally reduced efficiency at low and moderate angles of attack but improved performance at ۱۵° and ۲۰°. Overall, properly selected slot geometries can enhance aerodynamic performance at high angles of attack.

کلیدواژه ها:

NACA ۰۰۱۲ ، straight-slot ، CFD ، Angle of Attack ، lift-to-drag ratio