Aerodynamic Improvement of NACA ۴۴۱۲ Airfoil with Slot

In this study, the flow behavior around the NACA ۴۴۱۲ airfoil, with and without a surface slot, was investigated using two-dimensional numerical simulations. The main objective was to analyze the effect of local geometric modifications on aerodynamic performance, improve the lift-to-drag ratio (L/D), and delay stall. The results showed that introducing a slot from the lower to the upper surface of the airfoil enhances boundary layer energy and delays flow separation. At high angles of attack, the slotted airfoil exhibited higher lift coefficients and better aerodynamic performance compared to the baseline geometry, while the increase in drag at low angles remained minor and acceptable. Examination of pressure and velocity contours revealed that the slot produces a more uniform pressure distribution at the leading edge and reduces strong suction regions on the upper surface. This study demonstrates that local geometric modifications can be an effective strategy for improving the aerodynamic performance of airfoils operating near stall conditions.

کلیدواژه ها:

Airfoil ، NACA ۴۴۱۲ ، Numerical simulation ، Aerodynamic