In this thesis we worked with a simple model of fluid flow around an airfoil and attempted to find the relation between the lift coefficient and the angle of attack. We compared the theoretical flow with pictures of real flow that we took during an experiment in a wind tunnel. In our theoretical calculations we used the method of conformal mappings in combination with the Kutta condition. We analytically derived an expression for the lift coefficient with respect to the shape of the airfoil and the angle of attack. We found that our results matched very closely with the results of the similar panel method. Results obtained through CFD analysis and the experimental data, however, only matched our results for small angles of attack. The wind tunnel experiment also confirmed that the chosen model is only reliable for small angles of attack.
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