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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(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 |
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Polars for (goe460-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
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