Abstract
The boundary element method for numerically modeling linearized continuous media flows is considered. The method is one of the fastest among all computational aerodynamics methods. This is achieved by discarding the construction of three-dimensional computational grids, since the values to be determined during the solution of the flow problem are distributed along the surface of the layouts and, if necessary, along the surface of the vortex wake. This work is divided into the following stages: constructing a mathematical model of a complex-shaped surface and dividing it into panels, building a congruent grid on the surface, and calculating the aerodynamic characteristics of two aircraft. The results are obtained for Mach numbers corresponding to subsonic flows.
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