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NACA M6 AIRFOIL (m6-il)

NACA M6 AIRFOIL - NACA/Munk M-6 airfoil


Airfoil m6-il
Details Dat file Parser  
(m6-il) NACA M6 AIRFOIL
NACA/Munk M-6 airfoil
Max thickness 12% at 30% chord.
Max camber 2.2% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 
NACA M6 AIRFOIL
       17.       17.

  0.000000  0.000000
  0.012500  0.019700
  0.025000  0.028100
  0.050000  0.040300
  0.075000  0.049400
  0.100000  0.057100
  0.150000  0.068200
  0.200000  0.075500
  0.300000  0.082200
  0.400000  0.080500
  0.500000  0.072600
  0.600000  0.060300
  0.700000  0.045800
  0.800000  0.030600
  0.900000  0.015500
  0.950000  0.008800
  1.000000  0.002600

  0.000000  0.000000
  0.012500 -0.017600
  0.025000 -0.022000
  0.050000 -0.027300
  0.075000 -0.030300
  0.100000 -0.032400
  0.150000 -0.034700
  0.200000 -0.036200
  0.300000 -0.037900
  0.400000 -0.039000
  0.500000 -0.039400
  0.600000 -0.038200
  0.700000 -0.034800
  0.800000 -0.028300
  0.900000 -0.017700
  0.950000 -0.010800
  1.000000 -0.002600
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Lednicer format dat file
Selig format dat file

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Polars for NACA M6 AIRFOIL (m6-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m6-il50,000930.1 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   m6-il50,000532 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m6-il100,000948.8 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m6-il100,000548.8 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m6-il200,000966.5 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m6-il200,000563.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m6-il500,000987.4 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m6-il500,000576.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m6-il1,000,000997 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m6-il1,000,000583.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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