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NACA 1412 (naca1412-il)

NACA 1412 - NACA 1412 airfoil


Airfoil naca1412-il
Details Dat file Parser  
(naca1412-il) NACA 1412
NACA 1412 airfoil
Max thickness 12% at 29.9% chord.
Max camber 1% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 1412
1.00000     0.00126
0.95025     0.00966
0.90040     0.01753
0.80058     0.03178
0.70061     0.04413
0.60051     0.05453
0.50029     0.06267
0.40000     0.06803
0.29925     0.06940
0.24889     0.06799
0.19857     0.06486
0.14833     0.05951
0.09824     0.05118
0.07330     0.04537
0.04845     0.03786
0.02378     0.02733
0.01158     0.01954
0.00000     0.00000
0.01342     -0.01830
0.02622     -0.02491
0.05155     -0.03318
0.07670     -0.03857
0.10176     -0.04242
0.15167     -0.04733
0.20143     -0.04986
0.25111     -0.05081
0.30075     -0.05064
0.40000     -0.04803
0.49971     -0.04321
0.59949     -0.03675
0.69939     -0.02913
0.79942     -0.02066
0.89960     -0.01141
0.94975     -0.00646
1.00000     -0.00126
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Polars for NACA 1412 (naca1412-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca1412-il50,000929.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1412-il50,000531.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1412-il100,000944.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1412-il100,000543 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1412-il200,000957.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1412-il200,000553.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1412-il500,000973.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1412-il500,000566 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1412-il1,000,000983.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1412-il1,000,000578.6 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
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