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FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)

FX 74-Cl5-140 MOD (smoothed) - Modified Wortmann FX 74-CL5-140 high lift airfoil


Airfoil fx74modsm-il
Details Dat file Parser  
(fx74modsm-il) FX 74-Cl5-140 MOD (smoothed)
Modified Wortmann FX 74-CL5-140 high lift airfoil
Max thickness 13.1% at 27.1% chord.
Max camber 9.7% at 41.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 74-Cl5-140 MOD  (smoothed)
       1.00000     0.00009
       0.99754     0.00189
       0.99070     0.00624
       0.98037     0.01150
       0.96698     0.01741
       0.95044     0.02402
       0.93064     0.03188
       0.90775     0.04001
       0.88202     0.04848
       0.85370     0.05718
       0.82309     0.06616
       0.79048     0.07549
       0.75616     0.08510
       0.72043     0.09482
       0.68359     0.10446
       0.64594     0.11385
       0.60778     0.12287
       0.56937     0.13137
       0.53099     0.13916
       0.49265     0.14604
       0.45435     0.15177
       0.41638     0.15606
       0.37887     0.15868
       0.34204     0.15944
       0.30609     0.15820
       0.27120     0.15493
       0.23760     0.14964
       0.20549     0.14243
       0.17504     0.13344
       0.14648     0.12292
       0.11999     0.11110
       0.09576     0.09826
       0.07395     0.08459
       0.05468     0.07030
       0.03811     0.05576
       0.02433     0.04145
       0.01338     0.02769
       0.00548     0.01518
       0.00098     0.00518
       0.00000    -0.00021
       0.00098    -0.00435
       0.00548    -0.00787
       0.01338    -0.00871
       0.02433    -0.00754
       0.03811    -0.00539
       0.05468    -0.00292
       0.07395    -0.00022
       0.09576     0.00270
       0.11999     0.00584
       0.14648     0.00921
       0.17504     0.01279
       0.20549     0.01651
       0.23760     0.02030
       0.27120     0.02410
       0.30609     0.02786
       0.34204     0.03152
       0.37887     0.03503
       0.41638     0.03832
       0.45435     0.04134
       0.49265     0.04400
       0.53099     0.04624
       0.56937     0.04801
       0.60778     0.04925
       0.64594     0.04992
       0.68359     0.04997
       0.72043     0.04936
       0.75616     0.04807
       0.79048     0.04608
       0.82309     0.04334
       0.85370     0.03978
       0.88202     0.03537
       0.90775     0.03013
       0.93064     0.02434
       0.95044     0.01851
       0.96698     0.01290
       0.98037     0.00756
       0.99070     0.00319
       0.99754     0.00068
       1.00000    -0.00003
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Polars for FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx74modsm-il50,00096.2 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74modsm-il50,000528.8 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx74modsm-il100,000941.7 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74modsm-il100,000558.1 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   fx74modsm-il200,000976.4 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74modsm-il200,000584.1 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx74modsm-il500,0009118.7 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74modsm-il500,0005119.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   fx74modsm-il1,000,0009152.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74modsm-il1,000,0005149.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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