INVESTIGATION OF FLOW FIELD OVER NACA4412 WITH A VORTEX GENERATOR

Numerical simulations of the flow over the NACA4412 airfoil are carried out with vortex generator attached over the airfoil. The simulations are made for different angle of attacks at Re= based on airfoil chord. The three dimensional Reynolds averaged Navier-Stokes equations together with the equation of Spalart-Allmaras turbulence model are solved here using the commercial software Fluent. The effect of the vortex generator on the airfoil is discussed in the paper along with its effect on the aerodynamic characteristics of the airfoil. At small angles of attack the VG has negative effect although very insignificant with a negligible decrease in lift and increase in drag. However significant effect was observed at higher angles of attack. The inclusion of VG on an airfoil will help us to have a better understanding of the flow with and without VG. This will enable the researchers in the design in modern aerospace vehicle