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NACA 23021 (naca23021-il)

NACA 23021 - NACA 23021 airfoil


Airfoil naca23021-il
Details Dat file Parser  
(naca23021-il) NACA 23021
NACA 23021 airfoil
Max thickness 21% at 30% chord.
Max camber 1.9% at 10% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 23021
1.0000     0.0022
0.9500     0.0153
0.9000     0.0276
0.8000     0.0505
0.7000     0.0709
0.6000     0.0890
0.5000     0.1040
0.4000     0.1149
0.3000     0.1206
0.2500     0.1205
0.2000     0.1180
0.1500     0.1119
0.1000     0.1003
0.0750     0.0913
0.0500     0.0793
0.0250     0.0641
0.0125     0.0487
0.0000     0.0000
0.0125     -0.0208
0.0250     -0.0314
0.0500     -0.0452
0.0750     -0.0555
0.1000     -0.0632
0.1500     -0.0751
0.2000     -0.0830
0.2500     -0.0876
0.3000     -0.0895
0.4000     -0.0883
0.5000     -0.0814
0.6000     -0.0707
0.7000     -0.0572
0.8000     -0.0413
0.9000     -0.0230
0.9500     -0.0130
1.0000     -0.0022
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Selig format dat file

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Polars for NACA 23021 (naca23021-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca23021-il50,000918.6 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23021-il50,000524.8 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23021-il100,000937 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23021-il100,000535.7 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23021-il200,000949.1 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23021-il200,000542.7 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23021-il500,000956.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23021-il500,000550.5 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23021-il1,000,000964.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23021-il1,000,000555.8 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
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