The phenomenon of aeroelasticity of aircraft engine blades requires detailed research, as it directly affects flight safety. This is especially true for long, wide-chord aircraft engine fan blades. In this paper, numerical modeling of aeroelastic oscillations of aircraft engine fan blades at low rotation speed is carried out. Numerical simulations were performed using the commercial software ANSYS Fluent, with the help of which the equations of unsteady viscous air flow were integrated, together with the equations of blade motion using proprietary software, which significantly accelerates the process of two-way coupling. The blade motion was modeled using the modal method for the first five natural oscillation forms and the corresponding natural frequencies. According to the results of the study, the energy method revealed the possibility of self-oscillations on the first natural form. The modeling of the coupled oscillations of the blade confirmed the existence of conditions for the appearance of self-oscillations on the first natural form.