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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(goe406-il) GOE 406 AIRFOIL | Gottingen 406 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe411-il) GOE 411 AIRFOIL | Gottingen 411 airfoil Max thickness 13.2% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe460-il) GOE 460 AIRFOIL | Gottingen 460 airfoil Max thickness 20.5% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe796-il) GOE 796 AIRFOIL | Gottingen 796 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe533-il) GOE 533 AIRFOIL | Gottingen 533 airfoil Max thickness 13.7% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe406-il,goe411-il,goe460-il,goe796-il,goe533-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe406-il | 50,000 | 9 | 17.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 50,000 | 5 | 34.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 100,000 | 9 | 54.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 100,000 | 5 | 53.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 200,000 | 9 | 75.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 200,000 | 5 | 68.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 500,000 | 9 | 94.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 500,000 | 5 | 89.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 1,000,000 | 9 | 114.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 1,000,000 | 5 | 112 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe411-il | 50,000 | 9 | 30.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 50,000 | 5 | 28 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe411-il | 100,000 | 9 | 40.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 100,000 | 5 | 34.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe411-il | 200,000 | 9 | 43.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 200,000 | 5 | 35.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe411-il | 500,000 | 9 | 45.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 500,000 | 5 | 42.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe411-il | 1,000,000 | 9 | 48.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe411-il | 1,000,000 | 5 | 53.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe460-il | 50,000 | 9 | 20.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe460-il | 50,000 | 5 | 25.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe460-il | 100,000 | 9 | 39.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe460-il | 100,000 | 5 | 34.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe460-il | 200,000 | 9 | 46.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe460-il | 200,000 | 5 | 39.4 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe460-il | 500,000 | 9 | 54.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe460-il | 500,000 | 5 | 50.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe460-il | 1,000,000 | 9 | 66.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe460-il | 1,000,000 | 5 | 57.5 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 50,000 | 9 | 32.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 50,000 | 5 | 35.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 100,000 | 9 | 55.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 100,000 | 5 | 55.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 200,000 | 9 | 78 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 200,000 | 5 | 73.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 500,000 | 9 | 105.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 500,000 | 5 | 90.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 1,000,000 | 9 | 122.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 1,000,000 | 5 | 105.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 50,000 | 9 | 10.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 50,000 | 5 | 29.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 100,000 | 9 | 46.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 100,000 | 5 | 54.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 200,000 | 9 | 73.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 200,000 | 5 | 75.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 500,000 | 9 | 106.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 500,000 | 5 | 102.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 1,000,000 | 9 | 131.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 1,000,000 | 5 | 121.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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