Abstarct: Abstract: Increasing the aerodynamic properties of the airfoil through reducing the drag force and controlling the flow separation is one of the most important goals that aerospace researchers are trying to achieve by using different methods. So far, a lot of research has been done on a passive method known as leading edge bumping. The idea of this method is baxsed on the morphology of the humpback whale's fins, which was first studied by biologists. In this research, which was conducted experimentally and in the wind tunnel, the effect of corrugation of the Naca 0012 airfoil on its aerodynamic characteristics has been studied. Also, for validation, the standard Naca0012 airfoil was made first and it was experimentally tested in the wind tunnel, then the wavy Naca0012 airfoil was made, which we designed the attack edge, the escape edge, the upper surface and the lower surface in a wavy shape. The obtained results were recorded in the range of Reynolds numbers of 15,000, 30,000 and 66,000 and then we drew comparison charts for validation. After these tests, the wavy airfoil at 15000 and 66000 Reynolds showed a very good aerodynamic performance compared to the simple Naka 0012 airfoil, so that we saw that at 15000 Reynolds at an angle of attack of 15 degrees, the airfoil had a coefficient of 0.22. Simple has reached 0.33 in the corrugated airfoil, which is about 50% more than the simple airfoil. Also, at Reynolds 66000, the drag coefficient after the angle of attack of 15 degrees has reached from 0.57 in the simple airfoil to 0.61 in the wavy airfoil, which is an increase of more than 7%.