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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(goe222-il) GOE 222 (MVA H.33) AIRFOIL | Gottingen 222 (MVA H.33) airfoil Max thickness 18.5% at 29.2% chord Max camber 7.2% at 49.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe222-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe222-il | 50,000 | 9 | 5.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 50,000 | 5 | 14.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 100,000 | 9 | 42.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 100,000 | 5 | 47.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 200,000 | 9 | 74.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 200,000 | 5 | 67.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 500,000 | 9 | 99.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 500,000 | 5 | 84.8 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 1,000,000 | 9 | 115.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 1,000,000 | 5 | 102 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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