A Solution to the Problem of Subsonic Flow Around an Airfoil by Two-Phase Viscous Compressible Flow Taking Account of Phase Interaction

Ensuring the safety of flights and the economic efficiency of aircraft sets the task for aircraft designers and manufacturers to improve aerodynamic characteristics of aircraft by arranging optimal flow around the fuselage and lifting airfoils for all possible compositions of approach flow components. Statistics show that the number of flight accidents arising due to harmful effects of the environment in the overall balance of accidents in aviation is very significant. As a rule, such incidents occur due to the formation of ice on airfoils of aircraft. Therefore, the study of the effect of icing on the aircraft’s aerodynamic characteristics, and the creation of mathematical models able to predict the shapes of ice accumulation as early as at the design stage are the tasks, the solution of which will greatly increase the safety of flights. In this paper, a mathematical model of the icing process occurring on airfoils is studied in a three-dimensional formulation based on the Navier-Stokes system of equations and taking into account the analysis of trajectories of supercooled droplets. The model is implemented using the FENSAP-ICE software package. The results of calculation of the icing profile NACA 0012 for various variants of flow are presented. The results are compared with the data of other authors.

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