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Thin airfoil theory is a simple conception of airfoils that describes angle of attack to lift for incompressible, inviscid flows. It was first devised by famous German-American mathematician Max Munk and therewithal refined by British aerodynamicist Hermann Glauertand others in the 1920s. The thin airfoil theory idealizes that the flow around an airfoil as two-dimensional flow around a thin airfoil. It can be conceived as addressing an airfoil of zero thickness and infinite wingspan. Thin airfoil theory was particularly citable in its day because it provided a well-established theoretical basis for the following important prominence of airfoils in two-dimensional flow like i) on a symmetric shape of airfoil which center of pressure and aerodynamic center remain exactly one quarter of the chord behind the leading edge, ii) on a cambered airfoil, the aerodynamic center lies exactly one quarter of the chord behind the leading edge and iii)the slope of the lift coefficient versus angle of attack line is two pi ( ) units per radian. The fundamental equation of Prandtl’s lifting-line theory; simply states that the geometric angle of attack is equal to the sum of the effective angle plus the induced angle of attack. And also omitted the theory of elliptical wing theory which indicates that the Elliptical wing has better flight performance than any other airfoil. In this experiment we made a model of elliptical wing and test in wind tunnel to get experimental value. We also analyze the model in simulation software for further knowledge. Comparing this practical and experimental value to other airfoil like Mosquito wing and NACA 64A012 airfoil for further research.

Study on Thin Airfoil Theory & Performance Test of Elliptical Wing as Compared to Model Mosquito Wing and NACA 64A012 Mod Airfoil