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# NACA4412 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.

![](/files/-Mh5CHx_ASQfTlxhayB2)

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.

<img src="/files/-Mh5CHxbsT4-RtS93pB9" alt="" data-size="original">&#x20;

Good agreement between the simulation and the experimental results is observed.

## Vortex particle wake

The image below compares a doublet wake and a vortex particle wake. The freestream velocity is  $$|\mathbf{V}\_{ref}|=1$$m/s and the angle of attack is 0 deg. The Rosenhead-Moore and the Gaussian kernels were used to regularize the vortex particles.

<figure><img src="/files/GAW3HFQRU1MaQmsE598U" alt=""><figcaption></figcaption></figure>

<figure><img src="/files/kEmzSywxRLcDELIiYTxF" alt=""><figcaption></figcaption></figure>

As observed from the integrated loads the CL and CD compare favourably between the doublet and the vortex particle wake. The solution is not sensitive to the choice of a regularization kernel.

## Files

{% file src="/files/-MgbFgz1ii0Spt8\_083l" %}

## References

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