Düşük reynolds sayisinda naca 0012 kanat profi̇li̇ni̇n aerodi̇nami̇k özelli̇kleri̇ üzeri̇ndeki̇ hücum kenar deği̇şi̇mi̇ni̇n etki̇si̇

In this study, it is aimed to enhance the aerodynamic performance of the NACA 0012 airfoil with the morphing leading edge method. The investigation was conducted using an airfoil with a chord length of 120 mm under Reynolds number conditions of Re = 105. In addition to the base airfoil, a MATLAB code was developed to generate modified airfoil geometries by specifying the deflection angle and the deflection initiation point (expressed as a percentage of the chord length) as input parameters. The computational analysis considered deflection angles of 2°, 4°, and 6°, initiated at 10%, 20%, and 30% of the chord length. All configurations were analyzed using ANSYS FLUENT and compared aerodynamically with the base case (0° deflection). The performance evaluation focused on maximizing lift coefficient (CL), minimizing drag coefficient (CD), and optimizing the lift-to-drag ratio (CL/CD) as a measure of aerodynamic efficiency. The results demonstrate that airfoils with 6° deflection achieved the highest aerodynamic efficiency relative to the base model in the post-stall regime (e.g., α = 18°), with observed reductions in laminar separation bubbles (LSB) and trailing-edge vortex intensity. At moderate angles of attack (α = 10°), airfoils with 4° deflection exhibited optimal performance, yielding a 73.61% improvement in CL/CD compared to the base model. While stall characteristics revealed limited improvement, all modified geometries demonstrated reduced drag compared to the base model.