DETACHED EDDY SIMULATIONS FOR AIRFOIL WITH ICE SHAPES

Numerical simulations using the Detached Eddy Simulation (DES) approach were conducted with the aim of improving the predictions of stall for iced airfoils. The WIND code with the DES methodology was first validated with a well-documented circular cylinder flow. The validation results were in good agreement with the experimental and previous numerical results for the time-averaged aerodynamic forces. The unsteady flow field pattern associated with separation was also captured with the WIND DES simulation. Based on these results, a method was established for iced airfoils. The DES computation for an iced NACA23012 airfoil shows a maximum lift coefficient and stall phenomenon qualitatively consistent with experiments, whereas RANS simulations of the same case failed to predict a maximum lift coefficient. Three-dimensional vortex shedding processes were reasonably captured and the surface pressure plateaus in the separation region after ice shape were reasonably predicted, however with some variations as compared to the experimental results.