Question: Given a rectangular wing of aspect ratio 6 and area of 600 sq ft. The wing section employed is an NACA-4412 airfoil with an

Given a rectangular wing of aspect ratio 6 and area of 600

Given a rectangular wing of aspect ratio 6 and area of 600 sq ft. The wing section employed is an NACA-4412 airfoil with an aerodynamic center at .24c and Cmac -.088. If the wing is balanced so that the c.g. lies on the wing chord but 6 in. ahead of the a.c., calculate the lift coefficient for which the wing would be in equilibrium (Cmeg = 0). Is this lift coefficient useful? Is the equilibrium statically stable? Calculate the position of the c.g. for equilibrium at CL = .4. Is this equilibrium statically stable? ==

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