Aha its an interesting problem I understand better your edit now We really need to write this article on Aircraft longitudinal equilibrium There are two distinct reasons why the CG may not coincide with the wing centre of lift   As you explain the wing centre of lift moves when equivalent air speed is varied and when flaps are deployed trim  Static stability is increased when the CG moves forward stability  In other words even if the wing centre of lift did not move say a flapless wing with symmetrical profile we would still want the CG ahead of the wing Otherwise we would need a disproportionate zerolift stabilizer to provide the required stability That is the reason why airliners still generate negative tail lift in cruise where the trim conditions are most favourable high equivalent speed clean wing  So does the wing centre of lift move ahead of the CG or do we position the CG ahead of the wing centre of lift Both I guess  In this light I think each of our article versions is too categorical Ill try to find a better compromise but feel free to edit right away