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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(goe601-il) GOE 601 AIRFOIL | Gottingen 601 airfoil Max thickness 16% at 39% chord Max camber 2.5% at 49% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe601-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe601-il | 50,000 | 9 | 25.2 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 50,000 | 5 | 28 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe601-il | 100,000 | 9 | 47.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 100,000 | 5 | 44.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe601-il | 200,000 | 9 | 69.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 200,000 | 5 | 57.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe601-il | 500,000 | 9 | 82.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 500,000 | 5 | 69 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe601-il | 1,000,000 | 9 | 91.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 1,000,000 | 5 | 82.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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