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N-22 (n22-il)

N-22 - N-22 airfoil


Airfoil n22-il
Details Dat file Parser  
(n22-il) N-22
N-22 airfoil
Max thickness 12.4% at 30% chord.
Max camber 4% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
N-22
1.0000     0.0040
0.9500     0.0173
0.9000     0.0306
0.8000     0.0551
0.7000     0.0768
0.6000     0.0957
0.5000     0.1104
0.4000     0.1201
0.3000     0.1242
0.2000     0.1201
0.1500     0.1128
0.1000     0.1013
0.0750     0.0933
0.0500     0.0825
0.0250     0.0666
0.0125     0.0558
0.0000     0.0337
0.0125     0.0170
0.0250     0.0115
0.0500     0.0062
0.0750     0.0032
0.1000     0.0016
0.1500     0.0003
0.2000     0.0000
0.3000     0.0005
0.4000     0.0015
0.5000     0.0024
0.6000     0.0030
0.7000     0.0032
0.8000     0.0024
0.9000     0.0012
0.9500     0.0005
1.0000     0.0000
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Lednicer format dat file
Selig format dat file

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Polars for N-22 (n22-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n22-il50,000924.3 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n22-il50,000536 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n22-il100,000951.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   n22-il100,000554.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n22-il200,000971.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n22-il200,000570.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n22-il500,000998.4 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   n22-il500,000594.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n22-il1,000,0009120.5 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n22-il1,000,0005112.8 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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