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

BE50 (original) (be50-il)

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


Airfoil be50-il
Details Dat file Parser  
(be50-il) BE50 (original)
Verbitsky BE50 free flight airfoil (original)
Max thickness 7.3% at 25% chord.
Max camber 4.1% at 45% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
BE50 (original)
   1.00000   0.00260
   0.95000   0.01270
   0.90000   0.02276
   0.80000   0.03956
   0.70000   0.05314
   0.60000   0.06489
   0.55000   0.06991
   0.50000   0.07407
   0.45000   0.07783
   0.40000   0.07992
   0.35000   0.08090
   0.30000   0.08126
   0.25000   0.08087
   0.20000   0.07837
   0.15000   0.07308
   0.10000   0.06403
   0.07500   0.05727
   0.05000   0.04838
   0.02500   0.03639
   0.01500   0.03011
   0.01000   0.02600
   0.00000   0.01271
   0.01000   0.00400
   0.01500   0.00274
   0.02500   0.00156
   0.05000   0.00003
   0.07500   0.00000
   0.10000   0.00053
   0.15000   0.00294
   0.20000   0.00571
   0.25000   0.00812
   0.30000   0.01048
   0.35000   0.01310
   0.40000   0.01617
   0.45000   0.01847
   0.50000   0.02021
   0.55000   0.02136
   0.60000   0.02129
   0.70000   0.01936
   0.80000   0.01492
   0.90000   0.00856
   0.95000   0.00471
   1.00000   0.00000
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Lednicer format dat file
Selig format dat file

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Polars for BE50 (original) (be50-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   be50-il50,000938.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   be50-il50,000543.1 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   be50-il100,000959.7 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   be50-il100,000559.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   be50-il200,000979.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   be50-il200,000573.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   be50-il500,0009102.1 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   be50-il500,000595.4 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   be50-il1,000,0009118.2 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   be50-il1,000,0005110.1 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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