well... here is the third simulation with the stab in a central location.....
the pressure differences net out to zero... this would be where there
are no net pitch forces....

Interesting to note that in all three simulations, the flow over the right stab aligns with the freestreem...
the flow over the left stab has a lot of spanwise flow... towards the root of the stab...
additionally... there is a large spanwise flow on the side of the fin/rudder on the "Suction" side of the fuselage...
In the high stab case, there appears to be some interaction with the low pressure generated at the leading
edge of the fin on the left side.... looks like a small high pressure on the left side of the rudder in the low stab case...
I will need to more closely interrogate these results....
though I can measure pressures on the tail that indicate forces consistant with what I have experienced,
I still can't explain the mechanisms that cause the Yaw-Pitch coupling....