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N-9 (n9-il)

N-9 - N-9 airfoil


Airfoil n9-il
Details Dat file Parser  
(n9-il) N-9
N-9 airfoil
Max thickness 8.5% at 30% chord.
Max camber 2.7% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
N-9
1.0000     0.0028
0.9500     0.0135
0.9000     0.0212
0.8000     0.0386
0.7000     0.0524
0.6000     0.0652
0.5000     0.0760
0.4000     0.0822
0.3000     0.0846
0.2000     0.0826
0.1500     0.0776
0.1000     0.0692
0.0750     0.0644
0.0500     0.0580
0.0250     0.0478
0.0125     0.0398
0.0000     0.0225
0.0125     0.0124
0.0250     0.0088
0.0500     0.0048
0.0750     0.0030
0.1000     0.0022
0.1500     0.0000
0.2000     0.0000
0.3000     0.0000
0.4000     0.0002
0.5000     0.0008
0.6000     0.0012
0.7000     0.0012
0.8000     0.0008
0.9000     0.0002
0.9500     0.0001
1.0000     0.0000
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Selig format dat file

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Polars for N-9 (n9-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n9-il50,000936.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n9-il50,000538.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n9-il100,000953.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   n9-il100,000551.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n9-il200,000968.1 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n9-il200,000563.4 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n9-il500,000984 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n9-il500,000578.3 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n9-il1,000,000996.6 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n9-il1,000,000592.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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