n63012a

NACA 63-012A airfoil

n63012a Airfoil (x,y) Co-ordinates

0 0
0.005 0.00973
0.0075 0.01173
0.0125 0.01492
0.025 0.02078
0.05 0.02895
0.075 0.03504
0.1 0.03994
0.15 0.04747
0.2 0.05287
0.25 0.05664
0.3 0.05901
0.35 0.05995
0.4 0.05957
0.45 0.05792
0.5 0.05517
0.55 0.05148
0.6 0.047
0.65 0.04186
0.7 0.03621
0.75 0.03026
0.8 0.02426
0.85 0.01826
0.9 0.01225
0.95 0.00625
1 0.00025
0.95 -0.00625
0.9 -0.01225
0.85 -0.01826
0.8 -0.02426
0.75 -0.03026
0.7 -0.03621
0.65 -0.04186
0.6 -0.047
0.55 -0.05148
0.5 -0.05517
0.45 -0.05792
0.4 -0.05957
0.35 -0.05995
0.3 -0.05901
0.25 -0.05664
0.2 -0.05287
0.15 -0.04747
0.1 -0.03994
0.075 -0.03504
0.05 -0.02895
0.025 -0.02078
0.0125 -0.01492
0.0075 -0.01173
0.005 -0.00973
0 0

n63012a Airfoil CAD files

DOWNLOAD FROM HERE