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NACA 4412 (naca4412-il)

NACA 4412 - NACA 4412 airfoil


Airfoil naca4412-il
Details Dat file Parser  
(naca4412-il) NACA 4412
NACA 4412 airfoil
Max thickness 12% at 30% chord.
Max camber 4% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 4412
1.0000     0.0013
0.9500     0.0147
0.9000     0.0271
0.8000     0.0489
0.7000     0.0669
0.6000     0.0814
0.5000     0.0919
0.4000     0.0980
0.3000     0.0976
0.2500     0.0941
0.2000     0.0880
0.1500     0.0789
0.1000     0.0659
0.0750     0.0576
0.0500     0.0473
0.0250     0.0339
0.0125     0.0244
0.0000     0.0000
0.0125     -0.0143
0.0250     -0.0195
0.0500     -0.0249
0.0750     -0.0274
0.1000     -0.0286
0.1500     -0.0288
0.2000     -0.0274
0.2500     -0.0250
0.3000     -0.0226
0.4000     -0.0180
0.5000     -0.0140
0.6000     -0.0100
0.7000     -0.0065
0.8000     -0.0039
0.9000     -0.0022
0.9500     -0.0016
1.0000     -0.0013
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Lednicer format dat file
Selig format dat file

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Polars for NACA 4412 (naca4412-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca4412-il50,000933.4 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4412-il50,000536.1 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4412-il100,000956.1 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4412-il100,000557.4 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4412-il200,000978.1 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4412-il200,000576.6 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4412-il500,0009107.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4412-il500,0005101.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4412-il1,000,0009129.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4412-il1,000,0005119.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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