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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(e399-il) EPPLER 399 AIRFOIL | Eppler E399 human powered aircraft airfoil Max thickness 14.8% at 29% chord Max camber 5.1% at 51.4% chord | Remove Airfoil details Airfoil plotter |
(s2091-il) S2091-101-83 | Selig S2091 low Reynolds number airfoil Max thickness 10.1% at 26% chord Max camber 3.7% at 39.5% chord | Remove Airfoil details Airfoil plotter |
(e377m-il) EPPLER 377 (MODIFIED) AIRFOIL | Eppler E377 (modified) ultralight airfoil Max thickness 3.8% at 6.1% chord Max camber 9.2% at 32.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e399-il,s2091-il,e377m-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e399-il | 50,000 | 9 | 6.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 50,000 | 5 | 16.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 100,000 | 9 | 46.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 100,000 | 5 | 54 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 200,000 | 9 | 83.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 200,000 | 5 | 85.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 500,000 | 9 | 127.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 500,000 | 5 | 123.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 1,000,000 | 9 | 161.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 1,000,000 | 5 | 142.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2091-il | 50,000 | 9 | 28.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2091-il | 50,000 | 5 | 38.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2091-il | 100,000 | 9 | 54.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2091-il | 100,000 | 5 | 57.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2091-il | 200,000 | 9 | 77.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2091-il | 200,000 | 5 | 76.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2091-il | 500,000 | 9 | 107.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2091-il | 500,000 | 5 | 99.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2091-il | 1,000,000 | 9 | 128.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2091-il | 1,000,000 | 5 | 116.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 50,000 | 9 | 17.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 50,000 | 5 | 36.8 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 100,000 | 9 | 61.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 100,000 | 5 | 63.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 200,000 | 9 | 86.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 200,000 | 5 | 86.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 500,000 | 9 | 117.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 500,000 | 5 | 115.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 1,000,000 | 9 | 142.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 1,000,000 | 5 | 137 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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