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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(goe622-il) GOE 622 AIRFOIL | Gottingen 622 airfoil Max thickness 8% at 30% chord Max camber 2.4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe622-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe622-il | 50,000 | 9 | 35.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 50,000 | 5 | 38.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe622-il | 100,000 | 9 | 53.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 100,000 | 5 | 52.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe622-il | 200,000 | 9 | 69.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 200,000 | 5 | 64.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe622-il | 500,000 | 9 | 88.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 500,000 | 5 | 75.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe622-il | 1,000,000 | 9 | 98.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 1,000,000 | 5 | 82 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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