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.