Modeling Ice Accretion: Full Integration into Navier-Stokes Solver

Ice accretion for the NACA 0012 and the SC 2110 airfoils was modeled for different steady and unsteady flow conditions and compared with available experimental data. A previously developed spatially marching scheme for ice accretion was recast as a time-marching algorithm, allowing reversed flow and radial flow to be readily handled. The simulation was carried out as a multi-step process where the flow field around the iced airfoil was recomputed periodically. A two-dimensional compressible Navier Stokes solver was used to obtain the flow field, followed by an Eulerian droplet model and an icing model based on the extended-Messinger model. The results show reasonable agreement with experimental data for most of the conditions tested. Iced airfoil results for the steady and the oscillating SC 2110 airfoil cases were compared and it was determined that the differences in the two cases are small. A short simulation for 120 seconds for the oscillating case was carried out which confirmed that the differences between the final ice shape for a steady and an oscillating case are negligible.