Computational 3-D Icing Results for Scaled DLR-F6 Geometry

Icing calculations are made for a flight size DLR-F 6 Drag Prediction Workshop model. 3-D Navier-Stokes solutions were generated with CFD++ flow solver using hybrid mesh consisting of tetrahedra and prism layers. Flow sol utions generated for aerodynamics are reused as icing inputs to Lewice3D to generate ice accretion predictions. Generic aerodynamics and sample ice shapes are presented showing the capability of the parallel Lewice3D software with commercially available flow solvers. Predicted ice shapes are remeshed and 2-D airfoil computations are presented for a clean and iced wing. Aerodynamic effects due to icing are shown along with comparisons to experimental data for a NACA 23012 iced airfoil. The methodology outlined shows the value of using CFD analysis as inputs to Lewice3D.