Study of aircraft aerodynamic characteristics with operation of its powerplant engines is a vital task. In this article we represent mathematical modeling of the aircraft flow with operation of its propeller. The considered mathematical model of the propeller is based on the vortex and momentum theory. Solution of the model problem of the flow behind the propeller allows obtaining of the fields of perturbed velocities in the vicinity of the aircraft and its aerodynamic characteristics. The proposed approach is aimed at simplification of the mathematical model and reduction of calculation time.

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In this article we consider one of the approaches aimed at reducing time of calculation of aerodynamic characteristics of the studied objects using discrete vortex method. Also, accuracy assessment of calculation of aerodynamic characteristics was performed.Analysis of the obtained dependences allows us to make a conclusion that the considered approach to the calculation of the functions of the mutual influence on the stages of formation of the system of linear algebraic equations, position of vortex sheet nodes as well as aerodynamic loads reduces hardware costs about three times, with a relative error of less than 4%.