That's not very correct. Keep in mind that image shows AC. There is also CP(center of pressure). AC has constant moment.
For a positive cambered airfoil, the moment is negative and results in a counter-clockwise rotation of the airfoil. With camber, an angle of attack can be determined for which the airfoil produces no lift, but the moment is still present! So for airplanes with regular wings the tail has to press down because wings will try to rotate counter-clockwise and CG is aft of AC and opposes rotation. If we move CG even further to the tail we reach NP(neutral point) where tail will need to produce no any down force.Stick forces will be very light, drag from the tail will be low but it will be rather complex for humans to control airplane. So usually CG is somewhere between AC and NP for human controlled aircraft but for flyby wire CG can even move past NP for fighters. If you move CG forward past AC that will add very high load on the tail so it will produce a lot of drag or can even stall. So generally speaking CG oxford books are correct.