NACA 2412 Airfoil M=2.0% P=40.0% T=12.0%
  1.000084  0.001257
  0.960418  0.009302
  0.920690  0.016915
  0.880902  0.024115
  0.841059  0.030912
  0.801165  0.037316
  0.761221  0.043331
  0.721232  0.048955
  0.681199  0.054182
  0.641125  0.059003
  0.601014  0.063400
  0.560867  0.067352
  0.520688  0.070831
  0.480481  0.073800
  0.440250  0.076218
  0.400000  0.078030
  0.359407  0.079060
  0.318802  0.079116
  0.278203  0.078099
  0.237637  0.075884
  0.197135  0.072304
  0.156741  0.067121
  0.116517  0.059960
  0.076565  0.050135
  0.037107  0.035947
  0.000000  0.000000
  0.042893 -0.028347
  0.083435 -0.035735
  0.123483 -0.039560
  0.163259 -0.041521
  0.202865 -0.042304
  0.242363 -0.042284
  0.281797 -0.041699
  0.321198 -0.040716
  0.360593 -0.039460
  0.400000 -0.038030
  0.439750 -0.036395
  0.479519 -0.034511
  0.519312 -0.032431
  0.559133 -0.030197
  0.598986 -0.027845
  0.638875 -0.025403
  0.678801 -0.022894
  0.718768 -0.020333
  0.758779 -0.017731
  0.798835 -0.015094
  0.838941 -0.012423
  0.879098 -0.009715
  0.919310 -0.006960
  0.959582 -0.004146
  0.999916 -0.001257