COORDINATES OF NACA AIRFOILS
Created by naca456, version 1.0 (4 January 2002) on 17:26  4Jan2002
Ralph L. Carmichael, Public Domain Aeronautical Software
NACA 0012                                                                       
Four-digit profile, t/c= 0.1200
No camber, symmetrical section
SYMMETRICAL AIRFOIL DEFINITION
        x         y        dy/dx
    1  0.000000  0.000000**********
    2  0.005000  0.012213  1.181943
    3  0.007500  0.014849  0.949756
    4  0.012500  0.018939  0.715872
    5  0.025000  0.026147  0.477496
    6  0.050000  0.035547  0.302886
    7  0.075000  0.041999  0.220769
    8  0.100000  0.046828  0.168746
    9  0.150000  0.053452  0.101782
   10  0.200000  0.057375  0.057703
   11  0.250000  0.059412  0.025238
   12  0.300000  0.060017 -0.000078
   13  0.350000  0.059486 -0.020472
   14  0.400000  0.058030 -0.037248
   15  0.450000  0.055807 -0.051257
   16  0.500000  0.052940 -0.063111
   17  0.550000  0.049524 -0.073282
   18  0.600000  0.045634 -0.082154
   19  0.650000  0.041325 -0.090059
   20  0.700000  0.036639 -0.097287
   21  0.750000  0.031603 -0.104106
   22  0.800000  0.026231 -0.110762
   23  0.850000  0.020526 -0.117491
   24  0.900000  0.014477 -0.124515
   25  0.950000  0.008066 -0.132051
   26  1.000000  0.001260 -0.140310
End of output for symmetrical airfoil