  Aerodynamic prediction of glaze ice accretion on airfoils and wing is studied
using the Reynolds-averaged Navier-Stokes method. Two separation fixed
turbulence models are developed considering the nonequilibrium characteristics
of turbulence. The key ad hoc fix is a term of the local ratio of turbulent
production to dissipation, which is used to amplify the destruction term of the
{\omega}-equation to increase the eddy viscosity in a separating shear layer of
the fully turbulent region. A shear stress limiter is adopted to appropriately
simulate the beginning process of the shear layer transition when the
turbulence is under development. The proposed separation fixed terms can be
easily implemented into current solvers. Two airfoils and a three-dimensional
swept wing with ice accretions are numerically tested using the modified
models. The results indicate that the separating shear layer fixes improve the
ability of the models in predicting the stall behavior at large angles of
attack. The simulated averaged flow field and turbulence intensity distribution
are consistent with experimental data.
