NASA/LANGLEY 64-012 AIRFOIL
       26.       26.

  0.000000  0.000000
  0.005000  0.009780
  0.007500  0.011790
  0.012500  0.014900
  0.025000  0.020350
  0.050000  0.028100
  0.075000  0.033940
  0.100000  0.038710
  0.150000  0.046200
  0.200000  0.051730
  0.250000  0.055760
  0.300000  0.058440
  0.350000  0.059780
  0.400000  0.059810
  0.450000  0.057980
  0.500000  0.054800
  0.550000  0.050560
  0.600000  0.045480
  0.650000  0.039740
  0.700000  0.033500
  0.750000  0.026950
  0.800000  0.020290
  0.850000  0.013820
  0.900000  0.007860
  0.950000  0.002880
  1.000000  0.000000

  0.000000  0.000000
  0.005000 -0.009780
  0.007500 -0.011790
  0.012500 -0.014900
  0.025000 -0.020350
  0.050000 -0.028100
  0.075000 -0.033940
  0.100000 -0.038710
  0.150000 -0.046200
  0.200000 -0.051730
  0.250000 -0.055760
  0.300000 -0.058440
  0.350000 -0.059780
  0.400000 -0.059810
  0.450000 -0.057980
  0.500000 -0.054800
  0.550000 -0.050560
  0.600000 -0.045480
  0.650000 -0.039740
  0.700000 -0.033500
  0.750000 -0.026950
  0.800000 -0.020290
  0.850000 -0.013820
  0.900000 -0.007860
  0.950000 -0.002880
  1.000000  0.000000