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

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naca0015_wing.zip

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References

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