Question

1) Given a rectangular wing of aspect ratio 6 and area of 600 ft². The wing section employed is an NACA-4412 airfoil with an aerodynamic center at 0.24c and Cm ac=

-0.088. 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/lift coefficient for which the wing would be in equilibrium (Cmcg=0). Is this lift coefficient useful? Is the equilibrium statically stable? Calculate the position of the c.g. for equilibrium at CL=0.4. Is this equilibrium statically stable?

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