Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(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 | Remove Airfoil details Airfoil plotter |
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Polars for (be50sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| be50sm-il | 50,000 | 9 | 38.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 50,000 | 5 | 43 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 100,000 | 9 | 60.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 100,000 | 5 | 59.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 200,000 | 9 | 81.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 200,000 | 5 | 74.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 500,000 | 9 | 104.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 500,000 | 5 | 97.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 1,000,000 | 9 | 121.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 1,000,000 | 5 | 115.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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