Method of boundary elements for solution of aerodynamics design problem

In present work the method of boundary elements based on linearization of model continuous media is considered. The method provides one of the highest levels of computation speed among all approaches of computational aerodynamics. It is reached thanks to refusal of construction of spatial grids as the values which are subject to definition are distributed along a surface of configurations and, if it is necessary, on a surface of a wake vortex. The given work was subdivided into following stages: construction of geometry of the complex form and its splitting into panels, construction of the coordinated grid on surfaces, calculation of aerodynamic characteristics of two geometries. Results are received for the Mach numbers corresponding to subsonic flow.