Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

This research modifies the leading-edge structure of NACA 0015 and 4415 to resemble nose a beluga whale. The focus this modification is improve airfoil's aerodynamic performance investigate changing fluid flow patterns. Numerical equation used RANS combined with k-ε turbulence model. Mesh independence test shows that mesh 200 elements best mesh. Validation results reveal CFD data can follow trend experimental data, especially on AoA before stall. There was significant increase in Cl from at AoA>9°. On other hand, also had positive effect by lowering Cd value. provides an advantage increasing maximum Cl/Cd Furthermore, separation point delay airfoil. Modifications cause pressure lower side decrease upper side. Through velocity contours streamlines, modifications reduce recirculation area. Overall, modifying leading edge has impacts airfoils.