That one is a symmetrical airfoil, which produces zero lift at zero AOA.

For level flight, that airfoil must have enough incidence angle respect to the airstream (AOA) as to generate a lift force equal to the static weight of the airplane.

The tail should be pretty close to zero AOA at the same time, since it needs to push down in order to balance the whole plane.
The downwash of the wing will suffice to provide a slight negative AOA and push down force for the tail.

Here comes the balance act: too much AOA for the wing will induce too much lift and a higher angle of downwash on the tail: both of which will induce a nose up pitch.

The opposite will be true as well, requiring you to trim the elevator up to induce a higher AOA for the wing, and resulting in a plane that flies like it hangs the tail down.

I would recommend testing 2~3 degree of AOA for a relatively slow/heavy plane and less than that for faster/lighter ones.