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NACA 11-H-09 AIRFOIL (n11h9-il)

NACA 11-H-09 AIRFOIL - NACA 11-H-9 rotorcraft airfoil


Airfoil n11h9-il
Details Dat file Parser  
(n11h9-il) NACA 11-H-09 AIRFOIL
NACA 11-H-9 rotorcraft airfoil
Max thickness 9% at 40.2% chord.
Max camber 4.5% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 11-H-09 AIRFOIL
       19.       19.

 0.0000000 0.0000000
 0.0034000 0.0127000
 0.0078000 0.0174000
 0.0200000 0.0266000
 0.0447000 0.0400000
 0.0699000 0.0502000
 0.0952000 0.0585000
 0.1461000 0.0711000
 0.1973000 0.0799000
 0.2484000 0.0857000
 0.2996000 0.0889000
 0.4022000 0.0883000
 0.5039000 0.0772000
 0.6039000 0.0597000
 0.7029000 0.0391000
 0.8015000 0.0184000
 0.9001999 0.0017000
 0.9499000 0.0027000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0116000 -.0031000
 0.0171000 -.0031000
 0.0300000 -.0024000
 0.0552000 -.0009000
 0.0801000 -.0004000
 0.1048000 0.0013000
 0.1538000 0.0025000
 0.2027000 0.0028000
 0.2516000 0.0023000
 0.3004000 0.0014000
 0.3978000 -.0014000
 0.4961000 -.0051000
 0.5961000 -.0089000
 0.6970000 -.0117000
 0.7985000 -.0127000
 0.8998001 -.0105000
 0.9501000 -.0071000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 11-H-09 AIRFOIL (n11h9-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n11h9-il50,000924.5 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n11h9-il50,000524.6 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   n11h9-il100,000952.6 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n11h9-il100,000553.1 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   n11h9-il200,000979.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n11h9-il200,000579.1 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   n11h9-il500,0009114.5 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n11h9-il500,0005109.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n11h9-il1,000,0009138.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n11h9-il1,000,0005125 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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