Numerical investigation and parametric study of NACA 0009 airfoil with bumps inspired by mako-shark skin denticles

Abstract

In the current research, a numerical study of 53 airfoils inspired by the surface scales of the mako-shark skin based on NACA0009 airfoil has been performed. The airflow simulations were performed in different angles of attack from 4° to 11° and the validations are presented in two stages compared with two different studies. The diagrams of [Formula: see text] parameter, shear stress, pressure coefficient, and also the contours of velocity and streamlines are reported. The results of the lift, drag, and diagram of lift to drag ratios have been presented and analyzed for different geometries and angles of attack. The results show that by creating bumps’ pattern taken from the shark skin mounted over the suction side of the airfoils the ratio of lift to drag increases. For example up to 28% increment of average of Cl/Cd in the above mentioned range of angles of attack can be obtained utilizing just one bump with 0.7 mm thickness (0.7% of chord length) mounted at 23% of the chord on suction side.