What happens to the high pressure below an airfoil when the angle of attack increases? I recently came across this question in a principles of flight exam:

When the angle of attack of an airfoil increases


the high pressure below the airfoil increases, the induced drag increases
the high pressure below the airfoil decreases
the induced drag decreases
can't remember this option 


I chose 1. as the correct answer and it looks like I got it wrong. Although, I cannot tell for sure. 

I know the induced drag will increase, but will the high pressure underneath the airfoil increase or decrease with an increase in angle of attack?
I'm pretty sure you were right. More angle of attack means more lift. More lift is caused by higher pressure under the wing and lower pressure on top. More lift causes more induced drag.