naca0021 Airfoil

NACA 0021 airfoil

naca0021 Airfoil (x,y) Coordinates

1 0.00221
0.95 0.01412
0.9 0.02534
0.8 0.04591
0.7 0.06412
0.6 0.07986
0.5 0.09265
0.4 0.10156
0.3 0.10504
0.25 0.10397
0.2 0.1004
0.15 0.09354
0.1 0.08195
0.075 0.0735
0.05 0.06221
0.025 0.04576
0.0125 0.03315
0 0
0.0125 -0.03315
0.025 -0.04576
0.05 -0.06221
0.075 -0.0735
0.1 -0.08195
0.15 -0.09354
0.2 -0.1004
0.25 -0.10397
0.3 -0.10504
0.4 -0.10156
0.5 -0.09265
0.6 -0.07986
0.7 -0.06412
0.8 -0.04591
0.9 -0.02534
0.95 -0.01412
1 -0.00221

naca0021 Airfoil CAD files

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