Numerical Analysis of Naca0015 Airfoil Using Leasing Edge Rotating Cylinder

Abstract

The concept of boundary layer is prominent to study the flow behaviour around the airfoil at various angle of attack.. This study explores numerical simulation of conventional airfoil NACA0015 without vortex generator and with leading edge vortex generator. Two dimensional,steady low Reynold number flow have been investigated by solving Navier- stokes equation using ANASYS. Flow over airfoil have been analyzed keeping constant velocity of 27 m/s. To show the behaviour of airfoil at given boundary conditions k-ω SST turbulent model has been used as it is suitable for capturing flow behaviour at near boundary zones. The main objective is to increase the stalling angle by using rotating cylinder at the leading edge of airfoil NACA0015.From the results it was found that the rotating cylinder is an effective method in order to increase the lift of the airfoil at higher angles of attack.