# 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?

• If camber goes up? Camber is the curvature of the wing. It goes up when you extend slats or flaps. Angle of attack is the α in the first picture, and goes up by simply rotating the wing upwards. Commented May 24, 2019 at 23:09
• That's what I said in a simple way or whatever I'll just edit that out thanks for the notification. Commented May 24, 2019 at 23:22