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NACA 2412 (naca2412-il)

NACA 2412 - NACA 2412 airfoil


Airfoil naca2412-il
Details Dat file Parser  
(naca2412-il) NACA 2412
NACA 2412 airfoil
Max thickness 12% at 30% chord.
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 2412
1.0000     0.0013
0.9500     0.0114
0.9000     0.0208
0.8000     0.0375
0.7000     0.0518
0.6000     0.0636
0.5000     0.0724
0.4000     0.0780
0.3000     0.0788
0.2500     0.0767
0.2000     0.0726
0.1500     0.0661
0.1000     0.0563
0.0750     0.0496
0.0500     0.0413
0.0250     0.0299
0.0125     0.0215
0.0000     0.0000
0.0125     -0.0165
0.0250     -0.0227
0.0500     -0.0301
0.0750     -0.0346
0.1000     -0.0375
0.1500     -0.0410
0.2000     -0.0423
0.2500     -0.0422
0.3000     -0.0412
0.4000     -0.0380
0.5000     -0.0334
0.6000     -0.0276
0.7000     -0.0214
0.8000     -0.0150
0.9000     -0.0082
0.9500     -0.0048
1.0000     -0.0013
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Selig format dat file

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Polars for NACA 2412 (naca2412-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca2412-il50,000932.5 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2412-il50,000534.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2412-il100,000950 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2412-il100,000549.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2412-il200,000966.6 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2412-il200,000562.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2412-il500,000987.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2412-il500,000578.3 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2412-il1,000,0009101.4 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2412-il1,000,000587 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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