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# 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.

![](/files/-Mh5BRcffEXHQlWmCukM)

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.

<img src="/files/-Mh5BRckFuzWE4H19ZME" alt="" data-size="original"><img src="/files/-Mh5BRclPEZIkDD_i5cU" alt="" data-size="original"> <img src="/files/-Mh5BRcmA5vh_vz7Q_aV" alt="" data-size="original">&#x20;

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