n66021 Airfoil

NACA 66(4)-021 airfoil

n66021 Airfoil (x,y) Coordinates

0 0
0.005 0.01525
0.0075 0.01804
0.0125 0.0224
0.025 0.03045
0.05 0.04269
0.075 0.05233
0.1 0.06052
0.15 0.07369
0.2 0.08376
0.25 0.09153
0.3 0.09738
0.35 0.10154
0.4 0.10407
0.45 0.105
0.5 0.10434
0.55 0.10186
0.6 0.09692
0.65 0.08793
0.7 0.0761
0.75 0.06251
0.8 0.04796
0.85 0.03324
0.9 0.01924
0.95 0.00717
1 0
0.95 -0.00717
0.9 -0.01924
0.85 -0.03324
0.8 -0.04796
0.75 -0.06251
0.7 -0.0761
0.65 -0.08793
0.6 -0.09692
0.55 -0.10186
0.5 -0.10434
0.45 -0.105
0.4 -0.10407
0.35 -0.10154
0.3 -0.09738
0.25 -0.09153
0.2 -0.08376
0.15 -0.07369
0.1 -0.06052
0.075 -0.05233
0.05 -0.04269
0.025 -0.03045
0.0125 -0.0224
0.0075 -0.01804
0.005 -0.01525
0 0

n66021 Airfoil CAD files

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