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NACA 66(4)-221 (naca664221-il)

NACA 66(4)-221 - NACA 66(4)-221 airfoil


Airfoil naca664221-il
Details Dat file Parser  
(naca664221-il) NACA 66(4)-221
NACA 66(4)-221 airfoil
Max thickness 21% at 45% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 66(4)-221
1.00000     0.00000
0.95034     0.01032
0.90067     0.02440
0.85092     0.03996
0.80106     0.05591
0.75109     0.07145
0.70103     0.08581
0.65087     0.09823
0.60063     0.10763
0.55032     0.11281
0.50000     0.11537
0.44967     0.11595
0.39933     0.11478
0.34900     0.11183
0.29869     0.10709
0.24840     0.10047
0.19815     0.09170
0.14797     0.08039
0.09788     0.06565
0.07291     0.05653
0.04800     0.04580
0.02323     0.03226
0.01095     0.02342
0.00610     0.01869
0.00372     0.01570
0.00000     0.00000
0.00628     -0.01470
0.00890     -0.01729
0.01405     -0.02128
0.02677     -0.02854
0.05200     -0.03948
0.07709     -0.04805
0.10212     -0.05531
0.15203     -0.06693
0.20185     -0.07578
0.25160     -0.08257
0.30131     -0.08765
0.35100     -0.09123
0.40067     -0.09339
0.45033     -0.09405
0.50000     -0.09331
0.54968     -0.09091
0.59937     -0.08621
0.64913     -0.07763
0.69897     -0.06637
0.74891     -0.05355
0.79894     -0.03999
0.84908     -0.02650
0.89933     -0.01406
0.94966     -0.00400
1.00000     0.00000
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Selig format dat file

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Polars for NACA 66(4)-221 (naca664221-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca664221-il50,000916.5 at α=12.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca664221-il50,000512.2 at α=11.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca664221-il100,000919.1 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca664221-il100,000518.1 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   naca664221-il200,000929.6 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca664221-il200,000530.5 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca664221-il500,000968.6 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca664221-il500,000569.1 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca664221-il1,000,0009100.8 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca664221-il1,000,000591.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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