Adstract. Statement of the problem. The question of the qualitative and quantitative determination of the degree of negative influence of icing on the aircraft during the flight in adverse meteorological conditions, which has a specific layout, configuration and size, is quite complex and still remains far from completion. To solve this problem, an integrated approach based on the developed methodology and software support, which allows numerical simulation of the icing processes of the aerodynamic surfaces of aircraft has been proposed. When describing the airborne flow, an approach based on solving Reynolds-averaged Navier−Stokes equations using the Spalart−Allmaras turbulence model, in which the motion of supercooled water droplets is described using an interpenetrating media model, was proposed. Numerical simulation of the icing process on a streamlined surface was performed using the method of surface control volumes, based on the equations of continuity, conservation of momentum and energy. Calculation results. Systematic multiparameter studies of icing processes in a wide range of parameters using asan example of the NACA 0012 profile were carried out. Conclusions. The possibility of applying the obtained results in ensuring flight safety, designing deicing/antiicing protection systems, according to the regulatory documentation rules, was illustrated. Systematization of the results that can be obtained for a given aircraft, including one equipped with an ice protection system, will allow objectively, quickly and accurately analyze the danger of icing along the planned route during all phases of flight in known meteorological conditions, as well as during flight, using current data on the state of the atmosphere, to develop recommendations for changing the flight plan.