Is the aircraft neutral point a function of the tail incidence angle?
I have done some homework and I will explain why the Neutral point does not vary with the tail incidence angle.


The above equation is the fundamental equation defining the location of the neutral point. 

We can see that the Neutral point is a function of the following factors only,


Aerodynamic centre
Tail volume (Horizontal tail sizing and Arm length)
Tail efficiency factor (Ratio of dynamic pressure at the tail and at the wing),
Lift curve slope for the wing and HT (CLalpha - which is fixed and not dependent on the tail incidence),
Downwash effect
Fuselage moment contribution


So none of these factors are dependent on the tail incidence angle and hence there musnt be a change at all. What shocked me the most is the fact that errors in variable quantites can be accounted for but errors in quantities that shouldnt vary is very confusing. It is a very standard statement that '' Static margin or ultimately the Cmalpha shouldnt get affected by the change in tail incidence''
This is the information I could get about it.