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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(goe101-il) GOE 101 AIRFOIL | Gottingen 101 airfoil Max thickness 6.9% at 30% chord Max camber 4% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe565-il) GOE 565 AIRFOIL | Gottingen 565 airfoil Max thickness 8.4% at 30% chord Max camber 2.8% at 50% chord | Remove Airfoil details Airfoil plotter |
(e1211-il) EPPLER 1211 AIRFOIL | Eppler E1211 general aviation airfoil Max thickness 18% at 20.9% chord Max camber 4.4% at 37.7% chord | Remove Airfoil details Airfoil plotter |
(goe562-il) GOE 562 AIRFOIL | Gottingen 562 airfoil Max thickness 14.1% at 30% chord Max camber 6.3% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe101-il,goe565-il,e1211-il,goe562-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe101-il | 50,000 | 9 | 39.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 50,000 | 5 | 41.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 100,000 | 9 | 58.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 100,000 | 5 | 59.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 200,000 | 9 | 77.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 200,000 | 5 | 77.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 500,000 | 9 | 104.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 500,000 | 5 | 100.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 1,000,000 | 9 | 123.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 1,000,000 | 5 | 114.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe565-il | 50,000 | 9 | 37.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 50,000 | 5 | 39.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe565-il | 100,000 | 9 | 56.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 100,000 | 5 | 55 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe565-il | 200,000 | 9 | 76.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 200,000 | 5 | 69 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe565-il | 500,000 | 9 | 98.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 500,000 | 5 | 80.7 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe565-il | 1,000,000 | 9 | 110.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 1,000,000 | 5 | 89.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 50,000 | 9 | 6 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 50,000 | 5 | 24.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 100,000 | 9 | 33.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 100,000 | 5 | 44 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 200,000 | 9 | 58.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 200,000 | 5 | 62.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 500,000 | 9 | 89 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 500,000 | 5 | 89.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1211-il | 1,000,000 | 9 | 115.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1211-il | 1,000,000 | 5 | 113.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 50,000 | 9 | 9.2 at α=-4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 50,000 | 5 | 25.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 100,000 | 9 | 40.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 100,000 | 5 | 50 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 200,000 | 9 | 70.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 200,000 | 5 | 70.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 500,000 | 9 | 101.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 500,000 | 5 | 96.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 1,000,000 | 9 | 126.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 1,000,000 | 5 | 115.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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