Why is the angle of attack not proportional to the stagnation point? While I was studying my PPL today, I've encountered a question right below and I wasn't really satisfied with the answer.

Which statement about the airflow around an aerofoil is correct if the angle of attack increases?


The stagnation point moves up
The stagnation point moves down (correct answer)
The center of pressure moves down 
The center of pressure moves up 




Up here, α is the degree between the chord line and the oncoming airflow.



1) Stagnation point

2) Transition point

3) Transition point

4) Separation point

So, knowing all of these facts I just can't understand the question above. Why is the stagnation point moves down instead of going up while increasing the angle of attack?
From this site:



Notice that at low AoA the stagnation point is smack on the nose of the wing profile, while at higher AoA it is situated on the lower wing surface.

Hence: stagnation point location lowers with increasing AoA.