COORDINATES OF NACA AIRFOILS
Created by naca456, version 1.0 (4 January 2002) on 17:45  4Jan2002
Ralph L. Carmichael, Public Domain Aeronautical Software
NACA 63A010                                                                     
Six-series profile, family= 63a   t/c= 0.1000
No camber, symmetrical section
SYMMETRICAL AIRFOIL DEFINITION
        x         y        dy/dx
    1  0.000000  0.000000**********
    2  0.005000  0.008245  0.759116
    3  0.007500  0.009925  0.606350
    4  0.012500  0.012577  0.471300
    5  0.025000  0.017425  0.329752
    6  0.050000  0.024184  0.228396
    7  0.075000  0.029228  0.179546
    8  0.100000  0.033290  0.148174
    9  0.150000  0.039537  0.105060
   10  0.200000  0.044025  0.074979
   11  0.250000  0.047162  0.050751
   12  0.300000  0.049154  0.027881
   13  0.350000  0.049963  0.005420
   14  0.400000  0.049683 -0.015814
   15  0.450000  0.048355 -0.036303
   16  0.500000  0.046109 -0.053304
   17  0.550000  0.043073 -0.067842
   18  0.600000  0.039371 -0.080522
   19  0.650000  0.035109 -0.090756
   20  0.700000  0.030403 -0.096996
   21  0.750000  0.025423 -0.100879
   22  0.800000  0.020387 -0.100554
   23  0.850000  0.015347 -0.100507
   24  0.900000  0.010302 -0.103244
   25  0.950000  0.005233 -0.091571
   26  1.000000  0.000000 -6.108688
End of output for symmetrical airfoil