A simple answer:
Normally the wing has an upward force (lift) and the tail has a (usually) downward force (negative lift if you will). So as the aircraft increases airspeed, the lift of the wing, and the (usually) downward lift of the tail will increase. There are other factors which include the engine / prop orientation, center of mass, and so on.
The issue which makes a clear, always true, answer elusive is that the lift profile of the wing and of the tail are not the same. And of course there are complications from trim tabs and the like.
So when a designer considers pitch changes with airspeed changes, they usually try to minimize the effect to provide longitudinal stability. (Exceptions can be fighter, aerobatic and fly-by-wire configurations.) Another normal design goal is to have a lower angle of attack on the tail, than the wing. They can only be identical at more than one point, unless there is an unconventional or active flight control.