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PT40 (pt40-il)

PT40 - Great Plane PT-40 trainer airfoil


Airfoil pt40-il
Details Dat file Parser  
(pt40-il) PT40
Great Plane PT-40 trainer airfoil
Max thickness 11.6% at 27.1% chord.
Max camber 2.9% at 41.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
   PT40
 1.000000       0.001356
 0.997540       0.001963
 0.990700       0.003687
 0.980370       0.006189
 0.966980       0.009283
 0.950440       0.012906
 0.930640       0.016996
 0.907750       0.021447
 0.882020       0.026182
 0.853700       0.031153
 0.823090       0.036316
 0.790480       0.041628
 0.756160       0.047029
 0.720430       0.052435
 0.683590       0.057749
 0.645940       0.062857
 0.607780       0.067611
 0.569370       0.071880
 0.530990       0.075601
 0.492650       0.078789
 0.454350       0.081431
 0.416380       0.083445
 0.378870       0.084740
 0.342040       0.085252
 0.306090       0.084987
 0.271200       0.084026
 0.237600       0.082474
 0.205490       0.080395
 0.175040       0.077784
 0.146480       0.074578
 0.119990       0.070658
 0.095760       0.065886
 0.073950       0.060130
 0.054680       0.053385
 0.038110       0.046061
 0.024330       0.038699
 0.013380       0.030716
 0.005480       0.020620
 0.000980       0.008495
 0.000000      -0.000736
 0.000980      -0.009818
 0.005480      -0.021336
 0.013380      -0.030819
 0.024330      -0.037450
 0.038110      -0.040671
 0.054680      -0.041138
 0.073950      -0.040299
 0.095760      -0.039114
 0.119990      -0.037979
 0.146480      -0.036898
 0.175040      -0.035785
 0.205490      -0.034591
 0.237600      -0.033303
 0.271200      -0.031924
 0.306090      -0.030468
 0.342040      -0.028957
 0.378870      -0.027409
 0.416380      -0.025838
 0.454350      -0.024252
 0.492650      -0.022652
 0.530990      -0.021046
 0.569370      -0.019428
 0.607780      -0.017799
 0.645940      -0.016172
 0.683590      -0.014562
 0.720430      -0.012988
 0.756160      -0.011467
 0.790480      -0.010016
 0.823090      -0.008651
 0.853700      -0.007383
 0.882020      -0.006223
 0.907750      -0.005176
 0.930640      -0.004246
 0.950440      -0.003437
 0.966980      -0.002751
 0.980370      -0.002186
 0.990700      -0.001745
 0.997540      -0.001453
 1.000000      -0.001348
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Polars for PT40 (pt40-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   pt40-il50,000932.1 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   pt40-il50,000533.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   pt40-il100,000948.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   pt40-il100,000546.3 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   pt40-il200,000964.3 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pt40-il200,000557.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   pt40-il500,000978.8 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   pt40-il500,000576.1 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   pt40-il1,000,000995 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   pt40-il1,000,000589.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
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