# NACA0015 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
{% file src="/files/-MgbFgz0cKJZ5jUDS\_oA" %}
## References
\[1] McAlister, K.W. and Takahashi, R.K., "NACA 0015 Wing Pressure and Trailing Vortex Measurements", 1991
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