Numerical Simulations Of Iced Airfoils

The aerodynamic penalty due to airfoil icing accretion under two icing conditions are presented and analyzed. CFD methods including the use of Fluent software are utilized to investigate the flow field around the airfoil, the aerodynamic performances with respect to the increasing of ice layer during icing accretion. And lift, drag and stall characteristics of iced airfoil are summarized.In order to generate appropriate grid fitting the complex configuration of airfoil ice accretion, C-grid topology is adopted and the grid refinement in the leading edge is employed such that a sufficient grid resolution is obtained. During grid generation, an initial grid in boundary layer is first generated by algebraic method. Then the grid generation in the rest region is based on the solution of elliptic equations, so a high quality viscous structured grid generation is completed.Two dimensional Navier-Stokes solver based on Jameson's scheme in spatial discretisation and S-A one equation turbulence modelling is used for aerodynamic computation. Some acceleration techniques, including local time step, residual smoothing and preconditioning for low Mach number are applied to accelerate the convergence to the steady state. Based on above methodology, the study concerns with the impact on airfoil flow and aerodynamic performance due to ice accretion under two icing conditions by home-made solver and Fluent software. The qualitative and quantitative analyses and the comparison of different pressure distributions owing to various ice shapes are presented. The influence area and the penalty on lift and drag coefficients are determined. The result shows the great promising application of the methodology for practical engineering.