Considering the effect of the external aerodynamic force and skin heating

the computational model of stress inside ice on the leading edge of NACA 0012 airfoil was established according to the thermal de-icing physical process. The finite element method and triangular element were employed to solve the governing equations. The effects of external aerodynamic force and skin heating on the ice adhesion interface stress were obtained. The study showed that

without skin heating

the variation of airflow speed changed the intensity of interfacial stress of ice adhesion interface and the variation of angle of attack changed the distribution of interfacial stress of ice adhesion interface. An approximate linear increasing trend for maximum interfacial shear stress existed along with the increasing airflow speed. But external aerodynamic force contributed little to ice fracture. For skin heating

the coupled stress of ice adhesion interface and principal stress inside ice increased along with the increase of heat flow rate

which can be easily larger than the shear strength of adhesion interface and key factor for ice fracture. The preliminary ice fracture judgement criterion was founded based on the relationship between interfacial stress and adhesion strength related with interfacial temperature. Ice fracture appears when the sum of the interfacial stress generated by the external aerodynamic force and the interfacial thermal stress generated by the skin heating are greater than the shear strength related to the skin surface temperature. The fracture location is the area where the coupled stress exceeds the shear strength.