The main aim of the dissertation is to obtain distribution od circulation on the wing, the intensity of sources and dipoles on the body, and with the help of them gain coefficient of the total normal force of combination wing-body. The developed method relies on two different methods: Weissinger method for wing and the method of sources and dipoles for the body. Fluid flow around symmetrical wings simulate vortexes, while flow around body simulate inline sources and dipoles. Summing up with the potential flow from infinity, and setting boundary conditions of impermeability surfaces we are getting a mathematical model called dipoles-sources-vortices (DIV). We are gaining combination by setting mathematical metod so that we take influence of the vortex at checkpoints on wings and body, and influence of body at the checkpoint on wings and body. With velocity distribution at the control points on the body and wing, from Bernoulli equation can be determined distribution of pressures, and from them distribution of coefficient of lift for certain angles of attack. Model DIV developed in program package Matlab, is limited to a combination of trapezoidal profile symmetrical wings without dihedral and axisymetrical body at a low angle of attack. Results DIV models are compared with available experimental results and the results of other numerical models. This dissertation analyzes the influence of angle of the arrow wings to lift combination.