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NACA 6-H-10 AIRFOIL (n6h10-il)

NACA 6-H-10 AIRFOIL - NACA 6-H-10 rotorcraft airfoil


Airfoil n6h10-il
Details Dat file Parser  
(n6h10-il) NACA 6-H-10 AIRFOIL
NACA 6-H-10 rotorcraft airfoil
Max thickness 10% at 40% chord.
Max camber 4.6% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 6-H-10 AIRFOIL
       18.       18.

 0.0000000 -.0011400
 0.0125000 0.0191600
 0.0250000 0.0275900
 0.0500000 0.0386000
 0.0750000 0.0476000
 0.1000000 0.0560000
 0.1500000 0.0693800
 0.2000000 0.0794000
 0.2500000 0.0876900
 0.3000000 0.0920000
 0.4000000 0.0951700
 0.5000000 0.0853700
 0.6000000 0.0653000
 0.7000000 0.0411400
 0.8000000 0.0197100
 0.9000000 0.0057100
 0.9500000 0.0011000
 1.0000000 0.0000000

 0.0000000 -.0011400
 0.0125000 -.0039200
 0.0250000 -.0044900
 0.0500000 -.0046000
 0.0750000 -.0042800
 0.1000000 -.0033500
 0.1500000 -.0019800
 0.2000000 -.0016100
 0.2500000 -.0019900
 0.3000000 -.0030900
 0.4000000 -.0050000
 0.5000000 -.0097900
 0.6000000 -.0168000
 0.7000000 -.0228300
 0.8000000 -.0235600
 0.9000000 -.0130000
 0.9500000 -.0068000
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for NACA 6-H-10 AIRFOIL (n6h10-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n6h10-il50,000923.5 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h10-il50,000517.7 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n6h10-il100,000948.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h10-il100,000544.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n6h10-il200,000971.5 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h10-il200,000568.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n6h10-il500,000987 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h10-il500,000587.9 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n6h10-il1,000,0009107.3 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   n6h10-il1,000,000599.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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