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NACA 6-H-20 AIRFOIL (n6h20-il)

NACA 6-H-20 AIRFOIL - NACA 6-H-20 rotorcraft airfoil


Airfoil n6h20-il
Details Dat file Parser  
(n6h20-il) NACA 6-H-20 AIRFOIL
NACA 6-H-20 rotorcraft airfoil
Max thickness 20% at 40% chord.
Max camber 6.1% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 6-H-20 AIRFOIL
       18.       18.

 0.0000000 0.0000000
 0.0125000 0.0330000
 0.0250000 0.0470000
 0.0500000 0.0670000
 0.0750000 0.0830000
 0.1000000 0.0960000
 0.1500000 0.1196000
 0.2000000 0.1350000
 0.2500000 0.1470000
 0.3000000 0.1550000
 0.4000000 0.1610000
 0.5000000 0.1510000
 0.6000000 0.1210000
 0.7000000 0.0800000
 0.8000000 0.0410000
 0.9000000 0.0120000
 0.9500000 0.0053000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0150000
 0.0250000 -.0190000
 0.0500000 -.0230000
 0.0750000 -.0254000
 0.1000000 -.0275000
 0.1500000 -.0305000
 0.2000000 -.0320000
 0.2500000 -.0334000
 0.3000000 -.0356000
 0.4000000 -.0385000
 0.5000000 -.0430000
 0.6000000 -.0510000
 0.7000000 -.0570000
 0.8000000 -.0510000
 0.9000000 -.0230000
 0.9500000 -.0110000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 6-H-20 AIRFOIL (n6h20-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n6h20-il50,00093.5 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h20-il50,00056.1 at α=10.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n6h20-il100,00096 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h20-il100,00058.5 at α=15°Mach=0 Ncrit=5Xfoil predictionDetails
   n6h20-il200,000916.8 at α=16.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h20-il200,000514.2 at α=15°Mach=0 Ncrit=5Xfoil predictionDetails
   n6h20-il500,000967.6 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h20-il500,000550.5 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   n6h20-il1,000,000983 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h20-il1,000,000581.9 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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