Чисельний розрахунок аеродинамічної задачі підбору профілю крила для безпілотного літального апарату

The study analyzed and modeled using CAD and CAE technologies seven different aerodynamic profiles of the UAV wing at different angles of attack, using real profile models. For each geometry, a finite-volume model is built, in the Ansys software environment. The calculation was carried out in a 2D statement, in the Fluent module, since the analysis of the forces acting on the profile is carried out in the cross section of the wing. The dependence of the results of the desired values, such as, the lifting force, the lifting force coefficient, the drag force and the drag coefficient under given boundary conditions with a different angle of attack for the selected profiles, is demonstrated. The contours of static pressure and velocity at airflow of the NACA 2.5411 (naca2411-il) wing model at the angle of attack of 18 degrees are given. The best wing profile for an unmanned aerial vehicle was chosen, based on the obtained results.