Abstract
In the paper hereby, steady flow around a thin-walled wing is analysed by means of the Lifting Surface Method. In order to carry out tests, the wing has been divided into a finite number of quadrilateral panels. All panel edges in turn are replaced by discrete straight vortex segments which induce velocities within the flow field. The problem boils down to working out velocity circulation distribution on the wing surface. For this purpose, numerical realization has been developed in C by Minimalist GNU for Windows compiler and Code::Blocks IDE. To work out a solution to the linear non-homogeneous algebraic system, the Gauss – Seidel stationary iterative method has been applied. The obtained results for various angle of attack values are depicted by means of ParaView.
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