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?