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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(goe431-il) GOE 431 AIRFOIL | Gottingen 431 airfoil Max thickness 11.8% at 20% chord Max camber 7.2% at 60% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe431-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe431-il | 50,000 | 9 | 20.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 50,000 | 5 | 39.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe431-il | 100,000 | 9 | 62.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 100,000 | 5 | 55.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe431-il | 200,000 | 9 | 81 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 200,000 | 5 | 72.4 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe431-il | 500,000 | 9 | 104.7 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 500,000 | 5 | 85.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe431-il | 1,000,000 | 9 | 115.1 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 1,000,000 | 5 | 106.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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