Ok after crunching some numbers, here is what i have come up with.

span of the horizontal stab = 1.5ft
chord of the h stab = 9in

elevator ratio (precent of the stab that is an elevator) = 40

incidenc of the tail with respect to the fuesolage = +1.52deg

CGlocation = 30 percent chord, aft of the leading edge

nuteral point = 47 percent of the chord, aft of the leading edge (this represents the cg location at which the plane becomes unstable)

As for the verticle placement of the tail, keep it in line with the wing as much as possible, especially if you are doing some aerobatics.

If you can't make the tail to those specs then let me know what you are thinking of and i'll re-run the numbers if you like.

I make no guarentee that these numbers will yield an aircraft that will be perfect, they just represent my most accurate calculations using basic aerodynamic stability equations. These equations come from my coursework studying aerospace engineering, and have been proven through 4 competition aircraft to date.

If you have any other questions, let me know.
Nmking09