NACA 4424 Airfoil M=4.0% P=40.0% T=24.0%
  1.000333  0.002498
  0.989796  0.006962
  0.958533  0.019783
  0.907609  0.039374
  0.838857  0.063456
  0.754901  0.089405
  0.659129  0.114507
  0.555603  0.136083
  0.448922  0.151586
  0.342245  0.158362
  0.241113  0.152867
  0.152644  0.135302
  0.081629  0.107867
  0.031500  0.073918
  0.004140  0.037041
  0.000000  0.000000
  0.017713 -0.032730
  0.054954 -0.057561
  0.109354 -0.074230
  0.178225 -0.082812
  0.258887 -0.084117
  0.348738 -0.079848
  0.446549 -0.072092
  0.548926 -0.061235
  0.649888 -0.048901
  0.745099 -0.036627
  0.830274 -0.025422
  0.901408 -0.015936
  0.955012 -0.008671
  0.988351 -0.004075
  0.999667 -0.002498