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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(goe561-il) GOE 561 AIRFOIL | Gottingen 561 airfoil Max thickness 25% at 29.8% chord Max camber 10.2% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe561-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe561-il | 50,000 | 9 | 3.3 at α=-13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 50,000 | 5 | 5.7 at α=-8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe561-il | 100,000 | 9 | 8.4 at α=-8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 100,000 | 5 | 8.6 at α=-6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe561-il | 200,000 | 9 | 28.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 200,000 | 5 | 20.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe561-il | 500,000 | 9 | 43.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 500,000 | 5 | 33 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe561-il | 1,000,000 | 9 | 49.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe561-il | 1,000,000 | 5 | 42 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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