Numerical Analysis on Stall Suppression of a NACA 0012 Airfoil

Abstract

Stall suppression is vital during takeoff, maneuver, and landing. It becomes more crucial when the flow is at low Reynolds number as the separation of bubbles is commonly encountered. There are active and passive methods to control such separation and delay stall. For the present study burst control plates (BCPs) is used on upper surface of airfoil, which is a passive method. Two-dimensional symmetrical (National Advisory Committee for Aeronautics) NACA 0012 airfoil of chord (c) length 200 mm is numerically analyzed using ANSYS FLUENT at low Reynolds numbers of 1.3×105 with and without burst control plates for determine the aerodynamic characteristics. Initially mesh independence study is done at 8º angle of attack for different number of mesh elements. 408,400 number of mesh element is selected for further study. Transition SST model is used for numerical simulation studies of airfoil with BCPs as coefficient of lift agree very well with experimental data.