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N-11 (n11-il)

N-11 - N-11 airfoil


Airfoil n11-il
Details Dat file Parser  
(n11-il) N-11
N-11 airfoil
Max thickness 10.9% at 30% chord.
Max camber 4.4% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
N-11
1.0000     0.0020
0.9500     0.0165
0.9000     0.0300
0.8000     0.0524
0.7000     0.0732
0.6000     0.0898
0.5000     0.1026
0.4000     0.1108
0.3000     0.1128
0.2000     0.1082
0.1500     0.1008
0.1000     0.0890
0.0750     0.0800
0.0500     0.0694
0.0250     0.0540
0.0125     0.0430
0.0000     0.0230
0.0125     0.0094
0.0250     0.0060
0.0500     0.0022
0.0750     0.0006
0.1000     0.0000
0.1500     0.0002
0.2000     0.0014
0.3000     0.0034
0.4000     0.0048
0.5000     0.0056
0.6000     0.0060
0.7000     0.0050
0.8000     0.0034
0.9000     0.0016
0.9500     0.0008
1.0000     0.0000
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Selig format dat file

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Polars for N-11 (n11-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n11-il50,000927.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n11-il50,000538.1 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n11-il100,000954.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n11-il100,000556.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n11-il200,000975.6 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   n11-il200,000572 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n11-il500,0009100.9 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n11-il500,000593.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n11-il1,000,0009118.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n11-il1,000,0005111.6 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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