1) NACA 0012 AIRFOIL ANGLE OF ATTACK 0
NACA 0012 AIRFOIL ANGLE OF ATTACK 5
NACA 0012 AIRFOIL ANGLE OF ATTACK 10
As the pressure distribution becomes larger on the top of the airfoil, more lift is
generated.
2)
The angle of attack for the maximum L/D=10 degrees.
The stall angle is alpha= 16 degrees. On the L/D graph the y axis is decreasing
rapidly after the stall angle. The NACA 0012 airfoil is moderately efficient. The
L/D ratio is moderate but does not achieve very high L/D ratios like a cambered
airfoil. The drag rises quickly as the angle of attack gets bigger and this limits the
airfoils efficiency.