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N-10 (n10-il)

N-10 - N-10 airfoil


Airfoil n10-il
Details Dat file Parser  
(n10-il) N-10
N-10 airfoil
Max thickness 11.2% at 30% chord.
Max camber 3.6% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
N-10
1.0000     0.0034
0.9500     0.0174
0.9000     0.0296
0.8000     0.0510
0.7000     0.0712
0.6000     0.0874
0.5000     0.1010
0.4000     0.1088
0.3000     0.1124
0.2000     0.1096
0.1500     0.1022
0.1000     0.0914
0.0750     0.0842
0.0500     0.0738
0.0250     0.0594
0.0125     0.0492
0.0000     0.0300
0.0125     0.0158
0.0250     0.0114
0.0500     0.0068
0.0750     0.0042
0.1000     0.0026
0.1500     0.0000
0.2000     0.0000
0.3000     0.0002
0.4000     0.0006
0.5000     0.0012
0.6000     0.0014
0.7000     0.0010
0.8000     0.0008
0.9000     0.0004
0.9500     0.0002
1.0000     0.0000
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Lednicer format dat file
Selig format dat file

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Polars for N-10 (n10-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n10-il50,000928.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n10-il50,000537.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n10-il100,000952 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n10-il100,000552.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n10-il200,000968.6 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   n10-il200,000568.9 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   n10-il500,000995.3 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n10-il500,000592 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   n10-il1,000,0009115.7 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   n10-il1,000,0005109.4 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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