In this study, the aerodynamic characteristics of the humpback whale were investigated by applying the NACA-00 15 model to the wing of the airfoil. Inspired by the maneuverability during the chase and capture of the humpback whale, NACA-0015 has placed the tubercles the same wavelength (w) and different amplitudes (a) in the leading edge region of the wing. The three different modified wings and the baseline obtained were compared in terms of aerodynamic performance. The wavelength of the modified wings used in this study is 16% of the chord length and the values of the amplitudes were determined as 0,05%, 0, 1% and 0,15%, respectively, of the chord length. All wing structures were designed in Solidworks CAD program. These solid models were numerically analyzed with the k-epsilon realizable turbulence model in the average Navier-Stokes analysis method in ANSYS Fluent software. Wing openness ratio (aspect ratio) value 1,1 was selected. On the 7,2x 10(5) Reynolds number, analyzes were made on the wing at the attack angle between 0 degrees and 46 degrees. After the examination of the results, it's found that the baseline has a higher lift coefficient (C-L) than the modified wing before the stall. The coefficient of friction (C-D) of the 0,05a0,16w (0,05a ve 0,16w) is 12,57% lower than that of the baseline. For post-stall angle of attacks, when 0,05a0,16w wing is compared to baseline average C-L and C-D value, the wing of 0,5a0,16w has 7,86% and 9,79% higher values respectively. After stall, It has seen that the aerodynamic efficiency (C-L/C-D) of 0,05a0,16w is % 3,81 higher than the baseline.