ORIGINAL: Hossfly
The climb/descent of an airplane with a change in airspeed is simply an increase/decrease in the production of "lift" by the main wing in traditional convergent airflow. A lifting stab will not totally change that. It can help some but not adequately to rule out any change with aircraft velocity changes.
There is much more but not needed here.
The airfoil on the stab,if calculated properly it can become proportional, and lift the tailto change AOAcompensating for for added winglift at higher airspeeds. Thats fact and it is done on real aircraft.
The lift or negative lift is also there to compensate for center of lift changes (with airspeed) on swept back wings full size aircraft..
ORIGINAL: Hossfly
It does to a degree, However with any change in airspeed the lift of a lifting surface is increased by 1/2 of the square of the airspeed (airspeed being the actual flow of air molecules over the surface, known as Indicated Airspeed, NOT True Airspeed, Groundspeed, and/or Calibrated Airspeed) However the surfaces being different the change in lift-force produced with a change in airspeed is NOT directionally proportional.
Yourformula has to be for a particular airfoil at a specific AOA. At 0 deg.AOA the lift on a symetrical airfoil wont change at all with air speed, and it will gain proportionally withincreased AOA ultill stall.