Study of the flow around a NACA 0012 at different angles of attack at low Reynolds numbers

Abstract

In this study, the flow around a NACA 0012 airfoil at a very low Reynolds number (Re = 800, which is maintained constant) is solved using the solver Alya developed by the Barcelona Supercomputing Center (BSC). The cases of analysis are from α = 0 degrees to α = 18 degrees, in steps of 3 deg each time. The meshing software used is ICEM CFD for later exportation to Alya format. The results show a quite steady flow up to α = 12 deg, in which flux separation occurs and a unsteady vortex shedding pattern is observed. The aerodynamic coefficients behave the way it is expected for them, and no stall is observed throughout the entire range of angles of attack studied