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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(s1020-il) Ornithopter airfoil. | Selig S1020 ornithopter airfoil Max thickness 15.1% at 33.8% chord Max camber 4.6% at 57% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s1020-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1020-il | 50,000 | 9 | 6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1020-il | 50,000 | 5 | 18.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1020-il | 100,000 | 9 | 49.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1020-il | 100,000 | 5 | 53.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1020-il | 200,000 | 9 | 82.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1020-il | 200,000 | 5 | 81.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1020-il | 500,000 | 9 | 120 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1020-il | 500,000 | 5 | 111.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1020-il | 1,000,000 | 9 | 146.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1020-il | 1,000,000 | 5 | 127.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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