NACA 0012 Airfoil M=0.0% P=0.0% T=12.0%
  1.000000  0.001260
  0.960000  0.006737
  0.920000  0.011958
  0.880000  0.016939
  0.840000  0.021694
  0.800000  0.026231
  0.760000  0.030555
  0.720000  0.034666
  0.680000  0.038557
  0.640000  0.042218
  0.600000  0.045634
  0.560000  0.048782
  0.520000  0.051635
  0.480000  0.054158
  0.440000  0.056307
  0.400000  0.058030
  0.360000  0.059263
  0.320000  0.059928
  0.280000  0.059926
  0.240000  0.059131
  0.200000  0.057375
  0.160000  0.054418
  0.120000  0.049882
  0.080000  0.043072
  0.040000  0.032277
  0.000000  0.000000
  0.040000 -0.032277
  0.080000 -0.043072
  0.120000 -0.049882
  0.160000 -0.054418
  0.200000 -0.057375
  0.240000 -0.059131
  0.280000 -0.059926
  0.320000 -0.059928
  0.360000 -0.059263
  0.400000 -0.058030
  0.440000 -0.056307
  0.480000 -0.054158
  0.520000 -0.051635
  0.560000 -0.048782
  0.600000 -0.045634
  0.640000 -0.042218
  0.680000 -0.038557
  0.720000 -0.034666
  0.760000 -0.030555
  0.800000 -0.026231
  0.840000 -0.021694
  0.880000 -0.016939
  0.920000 -0.011958
  0.960000 -0.006737
  1.000000 -0.001260