with a NACA4412 airfoil is considered. Experiments of such wing were performed by R.M. Pinkerton  at different angles of attack. A structured mesh consisting of 1680 elements is used. The mesh is scaled so that the chord of the wing is
m and the span
m. The freestream velocity is set to
m/s. The image below shows the pressure coefficient distribution.
The image below shows the pressure coefficient at
for angle of attack
deg. The experimental results from Pinkerton  are shown for comparison.
Good agreement between the simulation and the experimental results is observed.
 Pinkerton, R. M. "Calculated and measured pressure distributions over the midspan section of the N.A.C.A 4412 airfoil", 1936