naca001034a08cli0.2 Airfoil

NACA 0010-34 a=0.8 c(li)=0.2 airfoil

naca001034a08cli0.2 Airfoil (x,y) Coordinates

1 0.001
0.95042 0.011
0.90076 0.02044
0.801 0.037
0.70064 0.04915
0.60031 0.05735
0.49994 0.06186
0.39955 0.06279
0.29917 0.0598
0.19886 0.05172
0.14876 0.04523
0.09875 0.03637
0.07378 0.03094
0.04887 0.02436
0.02407 0.01608
0.01176 0.01062
0.00687 0.0079
0 0
0.00813 -0.00632
0.01324 -0.0082
0.02593 -0.01186
0.05113 -0.01714
0.07622 -0.02122
0.10125 -0.02445
0.15124 -0.02961
0.20114 -0.03312
0.30083 -0.03684
0.40045 -0.03721
0.50006 -0.03526
0.59969 -0.03131
0.69936 -0.02549
0.799 -0.0183
0.89924 -0.01064
0.94958 -0.0061
1 -0.001

naca001034a08cli0.2 Airfoil CAD files

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