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Your Reynold number range is 50,000 to 1,000,000. (set)

BE50 (smoothed) (be50sm-il)

BE50 (smoothed) - Verbitsky BE50 free flight airfoil (original)


Airfoil be50sm-il
Details Dat file Parser  
(be50sm-il) BE50 (smoothed)
Verbitsky BE50 free flight airfoil (original)
Max thickness 7.3% at 23.8% chord.
Max camber 4% at 45.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
BE50 (smoothed)
       1.00000     0.00129
       0.99754     0.00178
       0.99070     0.00314
       0.98037     0.00517
       0.96698     0.00777
       0.95044     0.01091
       0.93064     0.01457
       0.90775     0.01865
       0.88202     0.02305
       0.85370     0.02766
       0.82309     0.03238
       0.79048     0.03710
       0.75616     0.04176
       0.72043     0.04627
       0.68359     0.05058
       0.64594     0.05463
       0.60778     0.05835
       0.56937     0.06171
       0.53099     0.06466
       0.49265     0.06714
       0.45435     0.06911
       0.41638     0.07054
       0.37887     0.07144
       0.34204     0.07186
       0.30609     0.07180
       0.27120     0.07119
       0.23760     0.06993
       0.20549     0.06792
       0.17504     0.06505
       0.14648     0.06128
       0.11999     0.05662
       0.09576     0.05113
       0.07395     0.04491
       0.05468     0.03812
       0.03811     0.03098
       0.02433     0.02374
       0.01338     0.01662
       0.00548     0.00989
       0.00098     0.00382
       0.00000    -0.00003
       0.00098    -0.00332
       0.00548    -0.00695
       0.01338    -0.00956
       0.02433    -0.01127
       0.03811    -0.01224
       0.05468    -0.01256
       0.07395    -0.01229
       0.09576    -0.01152
       0.11999    -0.01033
       0.14648    -0.00882
       0.17504    -0.00709
       0.20549    -0.00522
       0.23760    -0.00323
       0.27120    -0.00115
       0.30609     0.00102
       0.34204     0.00330
       0.37887     0.00563
       0.41638     0.00792
       0.45435     0.01002
       0.49265     0.01177
       0.53099     0.01310
       0.56937     0.01397
       0.60778     0.01440
       0.64594     0.01440
       0.68359     0.01402
       0.72043     0.01331
       0.75616     0.01233
       0.79048     0.01114
       0.82309     0.00980
       0.85370     0.00836
       0.88202     0.00688
       0.90775     0.00540
       0.93064     0.00398
       0.95044     0.00265
       0.96698     0.00146
       0.98037     0.00041
       0.99070    -0.00046
       0.99754    -0.00107
       1.00000    -0.00130
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Polars for BE50 (smoothed) (be50sm-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   be50sm-il50,000938.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   be50sm-il50,000543 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   be50sm-il100,000960.5 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   be50sm-il100,000559.2 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   be50sm-il200,000981.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   be50sm-il200,000574.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   be50sm-il500,0009104.9 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   be50sm-il500,000597.8 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   be50sm-il1,000,0009121.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   be50sm-il1,000,0005115.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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