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NACA 5-H-10 AIRFOIL (n5h10-il)

NACA 5-H-10 AIRFOIL - NACA 5-H-10 rotorcraft airfoil


Airfoil n5h10-il
Details Dat file Parser  
(n5h10-il) NACA 5-H-10 AIRFOIL
NACA 5-H-10 rotorcraft airfoil
Max thickness 9.9% at 40% chord.
Max camber 2.3% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 5-H-10 AIRFOIL
       18.       18.

 0.0000000 0.0000000
 0.0125000 0.0150000
 0.0250000 0.0210000
 0.0500000 0.0310000
 0.0750000 0.0380000
 0.1000000 0.0437000
 0.1500000 0.0530000
 0.2000000 0.0610000
 0.2500000 0.0660000
 0.3000000 0.0690000
 0.4000000 0.0720000
 0.5000000 0.0670000
 0.6000000 0.0550000
 0.7000000 0.0390000
 0.8000000 0.0200000
 0.9000000 0.0067000
 0.9600000 0.0027000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0093000
 0.0250000 -.0120000
 0.0500000 -.0150000
 0.0750000 -.0168000
 0.1000000 -.0185000
 0.1500000 -.0210000
 0.2000000 -.0230000
 0.2500000 -.0240000
 0.3000000 -.0250000
 0.4000000 -.0270000
 0.5000000 -.0280000
 0.6000000 -.0290000
 0.7000000 -.0290000
 0.8000000 -.0240000
 0.9000000 -.0110000
 0.9600000 -.0047000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 5-H-10 AIRFOIL (n5h10-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n5h10-il50,000930.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n5h10-il50,000531.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n5h10-il100,000948.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n5h10-il100,000548.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n5h10-il200,000965.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   n5h10-il200,000556.2 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n5h10-il500,000970 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n5h10-il500,000558.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n5h10-il1,000,000974.9 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n5h10-il1,000,000569 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
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