Wing Aerodynamic Performance Analysis and Stall Prediction Using CANICE2D-NS Icing Code

The paper presents results of iced airfoil performance in comparison to experimental data using a newly developed CFD based twodimensional ice accretion and anti-icing simulation code, CANICE2D-NS. In CANICE2D-NS, a Serial Multi-Block (SMB) Navier-Stokes CFD code has been coupled with the CANICE2D panel/boundary-layer method based icing code. The new coupling is being used for the flow analysis and performance prediction of iced airfoils. Results reinforce the benefits and the robustness of CFD based CANICE2D-NS icing code in predicting ice shapes, aerodynamic performance parameters such as lift and drag coefficients as well as iced airfoil surface pressure coefficient distribution. The results show good agreement with experimental data both in terms of predicted ice shapes as well as aerodynamic analysis of predicted and experimental ice shapes.