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NACA M6 (nacam6-il)

NACA M6 - NACA M6 airfoil


Airfoil nacam6-il
Details Dat file Parser  
(nacam6-il) NACA M6
NACA M6 airfoil
Max thickness 12% at 30% chord.
Max camber 2.1% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA M6
1.0000     0.0026
0.9500     0.0088
0.9000     0.0155
0.8000     0.0306
0.7000     0.0458
0.6000     0.0603
0.5000     0.0726
0.4000     0.0805
0.3000     0.0822
0.2500     0.0801
0.2000     0.0755
0.1500     0.0682
0.1000     0.0571
0.0750     0.0494
0.0500     0.0403
0.0250     0.0281
0.0125     0.0197
0.0000     0.0000
0.0125     -0.0176
0.0250     -0.0220
0.0500     -0.0273
0.0750     -0.0303
0.1000     -0.0324
0.1500     -0.0347
0.2000     -0.0362
0.2500     -0.0371
0.3000     -0.0379
0.4000     -0.0390
0.5000     -0.0394
0.6000     -0.0382
0.7000     -0.0348
0.8000     -0.0283
0.9000     -0.0177
0.9500     -0.0108
1.0000     0.0026
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Lednicer format dat file
Selig format dat file

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Polars for NACA M6 (nacam6-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   nacam6-il50,000930.5 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam6-il50,000532.2 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam6-il100,000949.9 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam6-il100,000549.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam6-il200,000967.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam6-il200,000564.8 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam6-il500,000989.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam6-il500,000572.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam6-il1,000,000990.6 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam6-il1,000,000581 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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