@Chris Scott
I TOLD you I shouldn't get involved in this discussion!
Don't take my words literally - I will change them to
"Chosen to obtain an acceptable floor cabin angle in cruise"
Now to take an airplane with which I know you are familiar but using approximate numbers, the no lift angle in cruise is just under 2 deg, the lift at zero aoa is about 0.23, and the lift curve slope about 0.12 per degree. The wing body setting is a little over 3.5 deg.
The optimum cruise CL is about 0.53, giving a cruise aoa of 2.5 deg which is familiar to you. Without the wing body setting it would be 6 deg.
To take the other example (different airplane) if the pitch is 2.7 and the indicated aoa -0.8 then the incident flow would be 1.9 deg nosedown at whatever point the vane is located. This seems to me to be quite possible