2. [25 points] A model wing of constant chord length is placed in a low-speed subsonic
wind tunnel, spanning the test section. The wing has a NACA 4412 and a chord length of
5 ft. The flow in the test section is at a velocity of 100 ft/sec and standard sea-level
conditions.
(a) [5 points] Determine the airfoil's maximum thickness, maximum camber, and
location of maximum camber;
(b) [12 points] If the lift per unit span is 30 lb (force), calculate the angle of attack
$\alpha$,
(c) [8 points] Calculate the drag per unit span and the pitching moment about the
airfoil's aerodynamic center per unit span at this angle of attack.
