NACA0015 wing

Example simulation of a wing

A rectangular wing of aspect ratio AR=6.576AR=6.576AR=6.576
 with a NACA0015 airfoil is considered. Experiments of such wing were performed by McAlister and Takahashi [1] at an angle of attack α=12\alpha=12α=12
deg and Reynolds number Re=2.5×106Re=2.5\times10^6Re=2.5×106
. A structured grid with 1680 elements is used. The grid is scaled so that the chord of the wing is cref=1c_{ref}=1cref​=1
m and the span bref=6.576b_{ref}=6.576bref​=6.576
m. The freestream velocity is set to ∣Vref∣=1|\mathbf{V}_{ref}|=1 ∣Vref​∣=1
m/s. The image below shows the pressure coefficient distribution.
The images below show the pressure coefficient at y/2b=0.3091y/2b=0.3091y/2b=0.3091
, y/2b=0.7825y/2b=0.7825y/2b=0.7825
, and y/2b=1.2166y/2b=1.2166y/2b=1.2166
. The experimental results from McAlister and Takahashi [1] are shown for comparison.
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Good agreement between the simulation and the experimental results is observed.
Files
naca0015_wing.zip
24KB
Binary
References
[1] McAlister, K.W. and Takahashi, R.K., "NACA 0015 Wing Pressure and Trailing Vortex Measurements", 1991

NACA4412 wing

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Last modified 2yr ago