NACA4412 wing
Example simulation of a wing
A rectangular wing of aspect ratio
$AR=6$
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
$c_{ref}=1$
m and the span
$b_{ref}=6$
m. The freestream velocity is set to
$|\mathbf{V}_{ref}|=1$
m/s. The image below shows the pressure coefficient distribution.
The image below shows the pressure coefficient at
$y/b=0$
for angle of attack
$\alpha=0$
deg. The experimental results from Pinkerton [1] are shown for comparison.
Good agreement between the simulation and the experimental results is observed.

# Files

naca4412_wing.zip
24KB
Binary

# References

[1] Pinkerton, R. M. "Calculated and measured pressure distributions over the midspan section of the N.A.C.A 4412 airfoil", 1936