NACA0015 wing
Example simulation of a wing
A rectangular wing of aspect ratio
AR=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=12
deg and Reynolds number
Re=2.5×106Re=2.5\times10^6
. A structured grid with 1680 elements is used. The grid is scaled so that the chord of the wing is
cref=1c_{ref}=1
m and the span
bref=6.576b_{ref}=6.576
m. The freestream velocity is set to
Vref=1|\mathbf{V}_{ref}|=1
m/s. The image below shows the pressure coefficient distribution.
The images below show the pressure coefficient at
y/2b=0.3091y/2b=0.3091
,
y/2b=0.7825y/2b=0.7825
, and
y/2b=1.2166y/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.

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