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NACA M20 AIRFOIL (m20-il)

NACA M20 AIRFOIL - NACA/Munk M-20 airfoil


Airfoil m20-il
Details Dat file Parser  
(m20-il) NACA M20 AIRFOIL
NACA/Munk M-20 airfoil
Max thickness 8.2% at 30% chord.
Max camber 6.1% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M20 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0170500
 0.0250000 0.0260000
 0.0500000 0.0417000
 0.0750000 0.0537000
 0.1000000 0.0647000
 0.1500000 0.0803000
 0.2000000 0.0914000
 0.3000000 0.1021000
 0.4000000 0.0999000
 0.5000000 0.0892000
 0.6000000 0.0730000
 0.7000000 0.0540000
 0.8000000 0.0350000
 0.9000000 0.0178000
 0.9500000 0.0106000
 1.0000000 0.0047000

 0.0000000 0.0000000
 0.0125000 -.0097500
 0.0250000 -.0094000
 0.0500000 -.0057000
 0.0750000 -.0013000
 0.1000000 0.0031000
 0.1500000 0.0103000
 0.2000000 0.0156000
 0.3000000 0.0206000
 0.4000000 0.0190000
 0.5000000 0.0133000
 0.6000000 0.0058000
 0.7000000 -.0012000
 0.8000000 -.0055000
 0.9000000 -.0056000
 0.9500000 -.0036000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M20 AIRFOIL (m20-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m20-il50,000910.4 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m20-il50,000526.7 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m20-il100,000955.9 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m20-il100,000556.3 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   m20-il200,000978.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m20-il200,000578 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   m20-il500,0009108.7 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m20-il500,0005105.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m20-il1,000,0009131.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m20-il1,000,0005125.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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