Aerodynamic Investigation of Triangular Vortex Generator over NACA 4415 Airfoil

Abstract

This paper presents a 2-dimensional computational analysis of  NACA 4415 Airfoil attached   with Triangular Vortex Generator(VG) to raiseit’s stalling angle. The aim of this study is to analysis the parameter such as Reynolds no. 2.18 x 105 and several angle of attack (AOA). In ansys fluent we have performed with C-H domain as enclosure specifying velocity-inlet and farfield as pressure-outlet. Airfoil is been implemented with Vortex Generator(triangular) to energize slow moving air above the airfoil by converting laminar to turbulent attached flow  and to have an intact airflow over boundary surface. Structured fine meshing is done to have a better convergence and by grid independence test it is been found that lift and drag coefficient is ceased with node exceeding 150000. The computational setup consists of incompressible, steady-state, Finite –element method(FEM) using standard K-Epsilon(2-equation) with wall function as near-wall treatment. The results shows that VG(triangular) equipped on NACA 4415 airfoil is reliable to regulate the boundary layer  by delaying  the flow separation. This results demonstrate that VG has proficiency of achieving lesser drag and higher lift to have a substantial maneuverability at higher stalling angle. The coefficient of lift(CL) maximum value for  airfoil equipped with (triangular) VG increase by 22.5%  and stalling angle postpone by 20o. Overall the attached Vortex Generator(VG) on airfoil contribute an augmented lift to drag ratio.