How does the pressure difference over a NACA 0012 affects its characteristics?

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I wanted to know how does the pressure difference (on the upper and lower surface) affect the performance of the airfoil? That is, if the pressure difference is high/low, how does that affect the characteristics of the airfoil, taking naca 0012 as example, for increased angle of attack, the pressure distibution vs x/c changes. How do we account for that?
Thank you
 

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As the angle of attack increases, the pressure difference between the upper and lower surface increases. The upper surface pressure drops very rapidly, for most airfoils this is most noticeable by observing the minimum pressure spike near the leading edge on the upper surface. This pressure difference creates lift. The pressure distribution can also create a torque on the airfoil which is referred to as the pitching moment.
 

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