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NACA 4421 (naca4421-il)

NACA 4421 - NACA 4421 airfoil


Airfoil naca4421-il
Details Dat file Parser  
(naca4421-il) NACA 4421
NACA 4421 airfoil
Max thickness 21% at 30% chord.
Max camber 4% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 4421
1.0000     0.0022
0.9500     0.0211
0.9000     0.0385
0.8000     0.0691
0.7000     0.0950
0.6000     0.1160
0.5000     0.1318
0.4000     0.1416
0.3000     0.1427
0.2500     0.1388
0.2000     0.1317
0.1500     0.1204
0.1000     0.1035
0.0750     0.0924
0.0500     0.0782
0.0250     0.0584
0.0125     0.0445
0.0000     0.0000
0.0125     -0.0242
0.0250     -0.0348
0.0500     -0.0478
0.0750     -0.0562
0.1000     -0.0615
0.1500     -0.0675
0.2000     -0.0698
0.2500     -0.0692
0.3000     -0.0676
0.4000     -0.0616
0.5000     -0.0534
0.6000     -0.0440
0.7000     -0.0335
0.8000     -0.0231
0.9000     -0.0127
0.9500     -0.0074
1.0000     -0.0022
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Selig format dat file

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Polars for NACA 4421 (naca4421-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca4421-il50,00093.6 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4421-il50,000515.3 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4421-il100,000936.1 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4421-il100,000541.9 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4421-il200,000961.2 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4421-il200,000558.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4421-il500,000983.3 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4421-il500,000578.1 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4421-il1,000,0009103.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4421-il1,000,000593.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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