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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(s5020-il) S5020 | Selig S5020 low Reynolds number airfoil Max thickness 8.4% at 27.8% chord Max camber 2.2% at 27.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s5020-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s5020-il | 50,000 | 9 | 25.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 50,000 | 5 | 33.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 100,000 | 9 | 46 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 100,000 | 5 | 48.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 200,000 | 9 | 64.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 200,000 | 5 | 63.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 500,000 | 9 | 88 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 500,000 | 5 | 82.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 1,000,000 | 9 | 104.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 1,000,000 | 5 | 96.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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