NACA 4424 Airfoil M=4.0% P=40.0% T=24.0%
  1.000333  0.002498
  0.996533  0.004116
  0.985178  0.008895
  0.966403  0.016614
  0.940438  0.026923
  0.907609  0.039374
  0.868347  0.053448
  0.823184  0.068583
  0.772756  0.084196
  0.717797  0.099699
  0.659129  0.114507
  0.597660  0.128044
  0.534364  0.139747
  0.470276  0.149085
  0.406471  0.155574
  0.342245  0.158362
  0.280350  0.156583
  0.222237  0.150271
  0.169078  0.139696
  0.121917  0.125342
  0.081629  0.107867
  0.048890  0.088043
  0.024173  0.066670
  0.007750  0.044498
 -0.000286  0.022138
  0.000000  0.000000
  0.008171 -0.020569
  0.023667 -0.038338
  0.046050 -0.053242
  0.074803 -0.065216
  0.109354 -0.074230
  0.149114 -0.080318
  0.193498 -0.083614
  0.241936 -0.084369
  0.293871 -0.082955
  0.348738 -0.079848
  0.406147 -0.075582
  0.466934 -0.070131
  0.528427 -0.063584
  0.589722 -0.056380
  0.649888 -0.048901
  0.707982 -0.041454
  0.763070 -0.034276
  0.814240 -0.027543
  0.860622 -0.021392
  0.901408 -0.015936
  0.935869 -0.011281
  0.963373 -0.007525
  0.983405 -0.004761
  0.995582 -0.003068
  0.999667 -0.002498