Static stability does not require a downward force on the horizontal tail if you care to read past the second chapter of any self respecting aerodynamics testbook.
In the first chapter, static stability is introduced with a nice little schematic of a CG ahead of the center of lift, and a downward force on the horizontal to balance the aircraft.
If you believe things are that simplistic, you are mistaken.
Most airplanes are perfectly stable with a small positive lift on the horizontal tail when the CG is near the aft limit. Think airfoil camber and pitching moment (nose down) for example, to give you a lead...