Thanks!
I am also wondering which position the stabilizer will go to in case you let go. In general the stabilizer provides a nose up moment (lift vector down) to counteract the pitch-down tendency of the whole aircraft due to the total lift working on a point aft of the ac CG.
But, I would say that it depends on the position of the center of pressure (CoP_stab) on the stabilizer with respect to its hinge point where it will move to. Assuming that the CoP_stab is aft of the hinge point, the stabilizer will move up (if you let go of it), reducing the negative lift force generated, causing the aircraft to pitch down. That in turn may be causing an increasing angle of attack on the stabilizer, and since its an inverted foil, this will increase negative lift again, causing a nose down moment? So it will find some equilibrium, or oscillate? Or will it end up at one of the mechanical stops?
I think this is a rather dynamic problem depending on many variables but maybe someone can shed light on this.
F. S.