NACA 0012 Airfoil M=0.0% P=0.0% T=12.0%
  1.000000  0.001260
  0.996057  0.001812
  0.984292  0.003443
  0.964888  0.006082
  0.938153  0.009619
  0.904508  0.013914
  0.864484  0.018809
  0.818712  0.024135
  0.767913  0.029717
  0.712890  0.035374
  0.654508  0.040917
  0.593691  0.046149
  0.531395  0.050854
  0.468605  0.054810
  0.406309  0.057789
  0.345492  0.059575
  0.287110  0.059980
  0.232087  0.058866
  0.181288  0.056160
  0.135516  0.051863
  0.095492  0.046049
  0.061847  0.038859
  0.035112  0.030473
  0.015708  0.021088
  0.003943  0.010884
  0.000000  0.000000
  0.003943 -0.010884
  0.015708 -0.021088
  0.035112 -0.030473
  0.061847 -0.038859
  0.095492 -0.046049
  0.135516 -0.051863
  0.181288 -0.056160
  0.232087 -0.058866
  0.287110 -0.059980
  0.345492 -0.059575
  0.406309 -0.057789
  0.468605 -0.054810
  0.531395 -0.050854
  0.593691 -0.046149
  0.654508 -0.040917
  0.712890 -0.035374
  0.767913 -0.029717
  0.818712 -0.024135
  0.864484 -0.018809
  0.904508 -0.013914
  0.938153 -0.009619
  0.964888 -0.006082
  0.984292 -0.003443
  0.996057 -0.001812
  1.000000 -0.001260