NACA4412 wing
Example simulation of a wing
A rectangular wing of aspect ratio
with a NACA4412 airfoil is considered. Experiments of such wing were performed by R.M. Pinkerton [1] 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 [1] are shown for comparison.

Good agreement between the simulation and the experimental results is observed.
naca4412_wing.zip
24KB
Binary
[1] Pinkerton, R. M. "Calculated and measured pressure distributions over the midspan section of the N.A.C.A 4412 airfoil", 1936
Last modified 1yr ago