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NACA 66 (p51htip-il)

NACA 66 - NACA 66


Airfoil p51htip-il
Details Dat file Parser  
(p51htip-il) NACA 66
NACA 66
Max thickness 12% at 45% chord.
Max camber 1.3% at 47.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 66,2-(1.8)12 A=.6 P-51 TIP AIRFOIL
      49.0      49.0

  0.000000  0.000000
  0.001859  0.006812
  0.004112  0.009583
  0.006512  0.011638
  0.008943  0.013306
  0.011393  0.014734
  0.018795  0.018227
  0.023749  0.020217
  0.048596  0.028646
  0.073528  0.035398
  0.098509  0.041094
  0.123521  0.046061
  0.148558  0.050417
  0.173613  0.054241
  0.198683  0.057614
  0.223765  0.060595
  0.248857  0.063218
  0.273958  0.065507
  0.299067  0.067478
  0.324183  0.069148
  0.349305  0.070531
  0.374432  0.071632
  0.399566  0.072452
  0.424704  0.072998
  0.449848  0.073258
  0.474998  0.073235
  0.500154  0.072920
  0.525318  0.072297
  0.550494  0.071343
  0.575689  0.070027
  0.600951  0.068244
  0.626185  0.065839
  0.651298  0.062766
  0.676347  0.059107
  0.701348  0.055022
  0.726309  0.050640
  0.751239  0.046002
  0.776140  0.041128
  0.801018  0.036064
  0.825880  0.030891
  0.850731  0.025693
  0.875577  0.020538
  0.900424  0.015492
  0.925280  0.010663
  0.950152  0.006221
  0.975052  0.002442
  0.985023  0.001227
  0.990012  0.000715
  1.000000  0.000000

  0.000000  0.000000
  0.003141 -0.006166
  0.005888 -0.008416
  0.008488 -0.009997
  0.011057 -0.011222
  0.013607 -0.012230
  0.021205 -0.014561
  0.026251 -0.015837
  0.051404 -0.021157
  0.076472 -0.025298
  0.101491 -0.028721
  0.126479 -0.031672
  0.151442 -0.034228
  0.176387 -0.036436
  0.201317 -0.038359
  0.226235 -0.040042
  0.251143 -0.041506
  0.276042 -0.042768
  0.300933 -0.043840
  0.325817 -0.044733
  0.350695 -0.045457
  0.375568 -0.046017
  0.400434 -0.046414
  0.425296 -0.046652
  0.450152 -0.046726
  0.475002 -0.046638
  0.499846 -0.046386
  0.524682 -0.045961
  0.549506 -0.045352
  0.574311 -0.044546
  0.599049 -0.043476
  0.623815 -0.042061
  0.648702 -0.040170
  0.673653 -0.037840
  0.698652 -0.035198
  0.723691 -0.032354
  0.748761 -0.029328
  0.773860 -0.026125
  0.798982 -0.022776
  0.824120 -0.019344
  0.849269 -0.015901
  0.874423 -0.012499
  0.899576 -0.009187
  0.924720 -0.006055
  0.949848 -0.003252
  0.974948 -0.001024
  0.984977 -0.000398
  0.989988 -0.000170
  1.000000  0.000000
Dat file parser warnings
  • Line 2 - Invalid characters : 2-(1.8)12 A=.6 P-51 TIP AIRFOIL
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Lednicer format dat file
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Polars for NACA 66 (p51htip-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   p51htip-il50,000922.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   p51htip-il50,000522.7 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   p51htip-il100,000935.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   p51htip-il100,000538.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   p51htip-il200,000952.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   p51htip-il200,000548 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   p51htip-il500,000972.9 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   p51htip-il500,000567 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   p51htip-il1,000,000990.8 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   p51htip-il1,000,000575.1 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
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