Aerodynamics of iced airfoil simulated by RANS code

In this work the numerical calculations were performed for two-dimensional flow around NACA23012 airfoil with and without ice accretion. Numerical calculations were performed with RANS (Reynolds Averaged Navier-Stokes) solver for incompressible flow with k-epsilon turbulence model (realizable version) implemented in Fluent software package. The calculated results were compared with experimentally determined data. The stall happens at much smaller angles of attack and also the slope of lift coefficient curve is smaller.