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NACA 0021 (naca0021-il)

NACA 0021 - NACA 0021 airfoil


Airfoil naca0021-il
Details Dat file Parser  
(naca0021-il) NACA 0021
NACA 0021 airfoil
Max thickness 21% at 30% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 0021
1.0000     0.00221
0.9500     0.01412
0.9000     0.02534
0.8000     0.04591
0.7000     0.06412
0.6000     0.07986
0.5000     0.09265
0.4000     0.10156
0.3000     0.10504
0.2500     0.10397
0.2000     0.10040
0.1500     0.09354
0.1000     0.08195
0.0750     0.07350
0.0500     0.06221
0.0250     0.04576
0.0125     0.03315
0.0000     0.00000
0.0125     -0.03315
0.0250     -0.04576
0.0500     -0.06221
0.0750     -0.07350
0.1000     -0.08195
0.1500     -0.09354
0.2000     -0.10040
0.2500     -0.10397
0.3000     -0.10504
0.4000     -0.10156
0.5000     -0.09265
0.6000     -0.07986
0.7000     -0.06412
0.8000     -0.04591
0.9000     -0.02534
0.9500     -0.01412
1.0000     -0.00221
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Lednicer format dat file
Selig format dat file

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Polars for NACA 0021 (naca0021-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca0021-il50,000919.1 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0021-il50,000525.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0021-il100,000936.6 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0021-il100,000535.6 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0021-il200,000948 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0021-il200,000543.6 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0021-il500,000960.6 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0021-il500,000556.8 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0021-il1,000,000974.7 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0021-il1,000,000571 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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