# 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. ![](https://81269019-files.gitbook.io/~/files/v0/b/gitbook-legacy-files/o/assets%2F-MV8htLPXN-_fWc_anY_%2F-Mh5A9-0BgU4nMJvUUiz%2F-Mh5BRcffEXHQlWmCukM%2Fnaca0015_wing_cp.png?alt=media\&token=ae2f4586-1374-4d91-b095-199ccbddf23e) 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="" %} ## References \[1] McAlister, K.W. and Takahashi, R.K., "NACA 0015 Wing Pressure and Trailing Vortex Measurements", 1991