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NACA 66 (p51hroot-il)

NACA 66 - NACA 66


Airfoil p51hroot-il
Details Dat file Parser  
(p51hroot-il) NACA 66
NACA 66
Max thickness 15.5% 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)15.5 A=.6 P-51 ROOT AIRFOIL
      49.0      49.0

  0.000000  0.000000
  0.001682  0.008603
  0.003870  0.012035
  0.006244  0.014564
  0.008658  0.016615
  0.011904  0.018371
  0.018467  0.022686
  0.023406  0.025158
  0.048200  0.035673
  0.073107  0.044072
  0.098080  0.051140
  0.123094  0.057294
  0.148140  0.062683
  0.173210  0.067405
  0.198300  0.071568
  0.223406  0.075244
  0.248524  0.078473
  0.273655  0.081290
  0.298795  0.083712
  0.323944  0.085764
  0.349102  0.087456
  0.374267  0.088803
  0.399439  0.089799
  0.424618  0.090457
  0.449804  0.090757
  0.474997  0.090707
  0.500199  0.090291
  0.525411  0.089490
  0.550637  0.088275
  0.575888  0.086589
  0.601224  0.084284
  0.626521  0.081158
  0.651662  0.077171
  0.676719  0.072485
  0.701715  0.067315
  0.726662  0.061803
  0.751567  0.055981
  0.776437  0.049884
  0.801278  0.043586
  0.826100  0.037195
  0.850910  0.030813
  0.875716  0.024511
  0.900523  0.018381
  0.925343  0.012562
  0.950185  0.007258
  0.975063  0.002806
  0.985028  0.001395
  0.990015  0.000806
  1.000000  0.000000

  0.000000  0.000000
  0.003318 -0.007958
  0.006130 -0.010868
  0.008756 -0.012924
  0.011342 -0.014531
  0.013906 -0.015867
  0.021533 -0.019020
  0.026594 -0.020778
  0.051800 -0.028184
  0.076893 -0.033973
  0.101920 -0.038767
  0.126906 -0.042950
  0.151860 -0.046494
  0.176790 -0.049600
  0.201700 -0.052313
  0.226594 -0.054690
  0.251476 -0.056761
  0.276345 -0.058552
  0.301205 -0.060074
  0.326056 -0.061348
  0.350898 -0.062382
  0.375733 -0.063188
  0.400561 -0.063760
  0.425382 -0.064111
  0.450196 -0.064225
  0.475003 -0.064110
  0.499801 -0.063757
  0.524589 -0.063154
  0.549363 -0.062284
  0.574112 -0.061180
  0.598776 -0.059516
  0.623479 -0.057380
  0.648338 -0.054575
  0.673281 -0.051217
  0.698285 -0.047492
  0.723338 -0.043517
  0.748433 -0.039370
  0.773563 -0.034881
  0.798722 -0.030297
  0.823900 -0.025648
  0.849090 -0.021021
  0.874284 -0.016472
  0.899477 -0.012076
  0.924657 -0.007953
  0.949815 -0.004289
  0.974937 -0.001389
  0.984972 -0.000565
  0.989985 -0.000261
  1.000000  0.000000
Dat file parser warnings
  • Line 2 - Invalid characters : 2-(1.8)15.5 A=.6 P-51 ROOT AIRFOIL
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Lednicer format dat file
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Polars for NACA 66 (p51hroot-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   p51hroot-il50,000920.3 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   p51hroot-il50,000519.5 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   p51hroot-il100,000932.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   p51hroot-il100,000527.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   p51hroot-il200,000942.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   p51hroot-il200,000543.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   p51hroot-il500,000967.2 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   p51hroot-il500,000555.6 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   p51hroot-il1,000,000970.1 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   p51hroot-il1,000,000546.5 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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