NACA4412 wing
Example simulation of a wing
A rectangular wing of aspect ratio
AR=6AR=6
with a NACA4412 airfoil is considered. Experiments of such wing were performed by R.M. Pinkerton [1] at different angles of attack. A structured mesh consisting of 1680 elements is used. The mesh is scaled so that the chord of the wing is
cref=1c_{ref}=1
m and the span
bref=6b_{ref}=6
m. The freestream velocity is set to
Vref=1|\mathbf{V}_{ref}|=1
m/s. The image below shows the pressure coefficient distribution.
The image below shows the pressure coefficient at
y/b=0y/b=0
for angle of attack
α=0\alpha=0
deg. The experimental results from Pinkerton [1] are shown for comparison.
Good agreement between the simulation and the experimental results is observed.

naca4412_wing.zip
24KB
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[1] Pinkerton, R. M. "Calculated and measured pressure distributions over the midspan section of the N.A.C.A 4412 airfoil", 1936
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