Panel method allows us to analyze fluid flow around airfoil, where nonviscous and incompressible fluid is assumed. Panel method can be used to analyze fluid flow around airfoil of any chosen shape. We can determine lift coefficient and doing so, we come close to real values (obtained with CFD analysis or experimentally) of lift coefficient at small angles of attack. In the thesis, panel method, used for modeling air flow around wing of aircraft, is described in detail and computation of lift coefficient as a function of angle of attack, obtained using panel method, is introduced. Afterward, we compute graph of lift coefficient as a function of angle of attack of chosen airfoil, and we compare the results with results of CFD (Computational Fluid Dynamics) and with experimentaly obtained values. We determine deviations of results of panel method and lastly we determine interval of panel method usage.
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