Okay, so here's a quick set of diagrams showing what I was saying.
The angle of incidence is the angle between the chord line of the wing and the longitudinal axis of the aircraft. (Figure 1)
Figure 2 shows a plane with no incidence to the wing or tail. This can work, but most airfoils perform better with a little incidence.
A thing I did not note on the drawing: the difference between the angle of incidence of the wing and the angle if incidence of the H-stab is called "decalage". The wing and the H-stab here have no decalage.
Figure 3 is shows a highly exaggerated incidence on the wing and no incidence on the tail. This plane has 9 degrees of wing incidence and -9 degrees of decalage. Looking at the picture it should be pretty obvious that the the tail would always be forcing the wing to a
high angle of attack in this configuration.
Figure 4 is a plane with the same 9 degrees of wing incidence but now it has the same 9 degrees of incidence on the horizontal stabilizer. That means it has 0 degrees of decalage and the wing/tail together would behave like the plane in Figure 2.
BUT, the plane would look like Figure 5 when flying straight and level. You can see how confusing it would be to have the fuselage pointing downward like that while the plane is flying straight and level.
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