Numerical analysis of convective heat transfer of airfoil ice protection area

Numerical analysis of convective heat transfer process was conducted to accurately describe the energy balance of the airfoil ice protection area. The convective heat transfer coefficient around the leading edge was calculated using four different turbulent models, including the Spalart-Allmaras model, the k-ε model, the k-ω model, and the transition SST model. Results were compared with icing tunnel tests conducted by NASA. The calculations were conducted under various y⁺ values. An abnormal minimum value of convective heat transfer intensity at the stagnation point is observed when the sparse mesh is employed, while the results of the case, in which the fine mesh (y⁺≈1) is used, match well with experimental data. Among the mentioned models, results of transition SST model shows the optimal agreement with experimental data.