A positively cambered wing with finite length L has its aerodynamic center AC located 25% from the wing's leading edge. What about the CG of the wing itself (not the CG of the whole plane)? Is there any recommendation for the wing's CG position along the chord?
What about the position of the AC along the wing's span axis? Should the AC be ideally located halfway at L/2 on the wing? What about the position of the wing's CG relative to AC? Should the CG also be at L/2? Why?