NACA0015 wing
Example simulation of a wing
A rectangular wing of aspect ratio
with a NACA0015 airfoil is considered. Experiments of such wing were performed by McAlister and Takahashi [1] at an angle of attack
deg and Reynolds number
. A structured grid with 1680 elements is used. The grid is scaled so that the chord of the wing is
m and the span
m. The freestream velocity is set to
m/s. The image below shows the pressure coefficient distribution.

The images below show the pressure coefficient at
,
, and
. The experimental results from McAlister and Takahashi [1] are shown for comparison.



Good agreement between the simulation and the experimental results is observed.
naca0015_wing.zip
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[1] McAlister, K.W. and Takahashi, R.K., "NACA 0015 Wing Pressure and Trailing Vortex Measurements", 1991
Last modified 2yr ago