For a stable conventional aircraft, center of gravity is aft of the
wing's center of lift. Horizontal tail also generates lift, which moves the
aircraft's center of lift aft of the center of gravity, giving the aircraft a margin of stability. If the horizontal tail is removed or destroyed while the aircraft is in level flight, the aircraft should pitch up uncontrollably. You can read this in any aeronautical engineering textbook.
Forgive my crude diagram:
A.C.(wing) A.C.(tail)
| | __
| A.C. |/ |
| | | |
____|_______|_____/|__|
/ _|__ o o |_ |
\__/____\_|________/__\|
|
|
C.G.
A.C. = Aerodynamic Center (center of lift) of the aircraft as a whole.
A.C.(wing) = Aerodynamic Center (center of lift) of the wing ONLY.
A.C.(tail) = Aerodynamic Center (center of lift) of the tail ONLY.
C.G. = Center of Gravity