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1- Calculate the coefficient of lift Cl? (Ignoring the axial force component, Airfoil profile and the shear stress distributions effects). 2- Find position of the centre of pressure. 3- Find location of stagnation point. 4- Find relation between center of pressure and Aerodynamic center for this airfoil. NACA 0012 airfoil a=9 Upper surface _ order panel 04 O Lower surface method Classical solution (from Ref. 10) -03 0/2