naca001264a08cli0.2 Airfoil

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

naca001264a08cli0.2 Airfoil (x,y) Coordinates

1 0.0012
0.9505 0.01271
0.90091 0.02355
0.8012 0.04253
0.70077 0.05663
0.60038 0.06662
0.49993 0.07157
0.39946 0.07279
0.299 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 0
0.01393 -0.00632
0.02664 -0.0082
0.05177 -0.01186
0.07678 -0.01714
0.10175 -0.02122
0.15161 -0.02445
0.20142 -0.02961
0.301 -0.03312
0.40054 -0.03684
0.50007 -0.03721
0.59962 -0.03526
0.69923 -0.03131
0.7988 -0.02549
0.89909 -0.0183
0.9495 -0.01064
1 -0.001

naca001264a08cli0.2 Airfoil CAD files

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