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NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il)

NACA 0012-64 a=0.8 c(li)=0.2 - NACA 0012-64 a=0.8 c(li)=0.2 airfoil


Airfoil naca001264a08cli02-il
Details Dat file Parser  
(naca001264a08cli02-il) NACA 0012-64 a=0.8 c(li)=0.2
NACA 0012-64 a=0.8 c(li)=0.2 airfoil
Max thickness 11% at 39.9% chord.
Max camber 1.8% at 29.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
 
NACA 0012-64 a=0.8 c(li)=0.2
1.00000     0.00120
0.95050     0.01271
0.90091     0.02355
0.80120     0.04253
0.70077     0.05663
0.60038     0.06662
0.49993     0.07157
0.39946     0.07279
0.29900     0.06974
0.19858     0.06221
0.14839     0.05645
0.09825     0.04832
0.07322     0.04295
0.04823     0.03623
0.02336     0.02659
0.01107     0.01928
0.00000     0.00000
0.01393     -0.00632
0.02664     -0.00820
0.05177     -0.01186
0.07678     -0.01714
0.10175     -0.02122
0.15161     -0.02445
0.20142     -0.02961
0.30100     -0.03312
0.40054     -0.03684
0.50007     -0.03721
0.59962     -0.03526
0.69923     -0.03131
0.79880     -0.02549
0.89909     -0.01830
0.94950     -0.01064
1.00000     -0.00100
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Polars for NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca001264a08cli02-il50,000933 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001264a08cli02-il50,000532.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001264a08cli02-il100,000949.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001264a08cli02-il100,000548.2 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001264a08cli02-il200,000966.9 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001264a08cli02-il200,000561.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001264a08cli02-il500,000980.7 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001264a08cli02-il500,000563.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001264a08cli02-il1,000,000977 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001264a08cli02-il1,000,000572.5 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
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