NACA0015 wing
Example simulation of a wing
A rectangular wing of aspect ratio
$AR=6.576$
with a NACA0015 airfoil is considered. Experiments of such wing were performed by McAlister and Takahashi [1] at an angle of attack
$\alpha=12$
deg and Reynolds number
$Re=2.5\times10^6$
. A structured grid with 1680 elements is used. The grid is scaled so that the chord of the wing is
$c_{ref}=1$
m and the span
$b_{ref}=6.576$
m. The freestream velocity is set to
$|\mathbf{V}_{ref}|=1$
m/s. The image below shows the pressure coefficient distribution.
The images below show the pressure coefficient at
$y/2b=0.3091$
,
$y/2b=0.7825$
, and
$y/2b=1.2166$
. The experimental results from McAlister and Takahashi [1] are shown for comparison.
Good agreement between the simulation and the experimental results is observed.

# Files

naca0015_wing.zip
24KB
Binary

# References

[1] McAlister, K.W. and Takahashi, R.K., "NACA 0015 Wing Pressure and Trailing Vortex Measurements", 1991