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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(fg3-il) Fage & Collins 3 | Fage & Collins 3 airfoil Max thickness 10.1% at 30% chord Max camber 4.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe417a-il) GOE 417A (GEW. PLATTE) AIRFOIL | Gottingen 417A (GEW. PLATTE) airfoil Max thickness 3.2% at 2.5% chord Max camber 5.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe683-il) GOE 683 AIRFOIL | Gottingen 683 airfoil Max thickness 19.9% at 30% chord Max camber 3% at 30% chord | Remove Airfoil details Airfoil plotter |
(e426-il) EPPLER 426 AIRFOIL | Eppler E426 airfoil Max thickness 10.8% at 25.5% chord Max camber 0.6% at 50.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fg3-il,goe417a-il,goe683-il,e426-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fg3-il | 50,000 | 9 | 32.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 50,000 | 5 | 35.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 100,000 | 9 | 48.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 100,000 | 5 | 49.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 200,000 | 9 | 65.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 200,000 | 5 | 65.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 500,000 | 9 | 90.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 500,000 | 5 | 89 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 1,000,000 | 9 | 111.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 1,000,000 | 5 | 108.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 50,000 | 9 | 46.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 50,000 | 5 | 45.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 100,000 | 9 | 65.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 100,000 | 5 | 56.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 200,000 | 9 | 71.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 200,000 | 5 | 61.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 500,000 | 9 | 75.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 500,000 | 5 | 68.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 1,000,000 | 9 | 86.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 1,000,000 | 5 | 116.9 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe683-il | 50,000 | 9 | 7.9 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 50,000 | 5 | 21.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe683-il | 100,000 | 9 | 31.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 100,000 | 5 | 41.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe683-il | 200,000 | 9 | 58.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 200,000 | 5 | 59.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe683-il | 500,000 | 9 | 85.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 500,000 | 5 | 70.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe683-il | 1,000,000 | 9 | 98.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 1,000,000 | 5 | 81.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e426-il | 50,000 | 9 | 22.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e426-il | 50,000 | 5 | 26.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e426-il | 100,000 | 9 | 33.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e426-il | 100,000 | 5 | 38.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e426-il | 200,000 | 9 | 48.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e426-il | 200,000 | 5 | 54.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e426-il | 500,000 | 9 | 74.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e426-il | 500,000 | 5 | 74.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e426-il | 1,000,000 | 9 | 92.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e426-il | 1,000,000 | 5 | 89 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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