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NACA4412 wing

Example simulation of a wing

A rectangular wing of aspect ratio AR=6AR=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}=1cref​=1
m and the span bref=6b_{ref}=6bref​=6
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 image below shows the pressure coefficient at y/b=0y/b=0y/b=0
 for angle of attack α=0\alpha=0α=0
deg. The experimental results from Pinkerton [1] are shown for comparison.
​
 
Good agreement between the simulation and the experimental results is observed.
Files
naca4412_wing.zip
24KB
Binary
References
[1] Pinkerton, R. M. "Calculated and measured pressure distributions over the midspan section of the N.A.C.A 4412 airfoil", 1936

Ellipsoid

NACA0015 wing

Last modified 2yr ago