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NACA 63(4)-221 (naca634221-il)

NACA 63(4)-221 - NACA 63(4)-221 airfoil


Airfoil naca634221-il
Details Dat file Parser  
(naca634221-il) NACA 63(4)-221
NACA 63(4)-221 airfoil
Max thickness 21% at 34.9% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 63(4)-221
1.00000     0.00000
0.95018     0.00708
0.90039     0.01629
0.85056     0.02693
0.80067     0.03849
0.75073     0.05054
0.70071     0.06262
0.65063     0.07426
0.60048     0.08512
0.55027     0.09485
0.50000     0.10309
0.44969     0.10949
0.39934     0.11369
0.34897     0.11529
0.29860     0.11383
0.24824     0.10946
0.19792     0.10204
0.14767     0.09111
0.09753     0.07593
0.07253     0.06601
0.04763     0.05375
0.02292     0.03757
0.01075     0.02628
0.00600     0.02001
0.00367     0.01627
0.00000     0.00000
0.00633     -0.01527
0.00900     -0.01861
0.01425     -0.02414
0.02708     -0.03385
0.05237     -0.04743
0.07747     -0.05753
0.10247     -0.06559
0.15233     -0.07765
0.20208     -0.08612
0.25176     -0.09156
0.30140     -0.09439
0.35103     -0.09469
0.40066     -0.09227
0.45031     -0.08759
0.50000     -0.08103
0.54973     -0.07295
0.59952     -0.06370
0.64937     -0.05366
0.69929     -0.04318
0.74927     -0.03264
0.79933     -0.02257
0.84944     -0.01347
0.89961     -0.00595
0.94982     -0.00076
1.00000     0.00000
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Selig format dat file

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Polars for NACA 63(4)-221 (naca634221-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca634221-il50,00094.8 at α=-3°Mach=0 Ncrit=9Xfoil predictionDetails
   naca634221-il50,000510.8 at α=14.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca634221-il100,000928.9 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   naca634221-il100,000534 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca634221-il200,000958.1 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca634221-il200,000558.4 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca634221-il500,000988 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca634221-il500,000582 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca634221-il1,000,0009108 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca634221-il1,000,000595.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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