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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(goe122-il) GOE 122 (MVA H.2) AIRFOIL | Gottingen 122 (MVA H.2) airfoil Max thickness 7.3% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe122-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe122-il | 50,000 | 9 | 37.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 50,000 | 5 | 39.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 100,000 | 9 | 55.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 100,000 | 5 | 56.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 200,000 | 9 | 73.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 200,000 | 5 | 72.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 500,000 | 9 | 95.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 500,000 | 5 | 89.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 1,000,000 | 9 | 110.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 1,000,000 | 5 | 97.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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