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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(goe300-il) GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL | Gottingen 300 (Friedrichshafen G20) airfoil Max thickness 8.4% at 30% chord Max camber 6.7% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe300-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe300-il | 50,000 | 9 | 19.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 50,000 | 5 | 38.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe300-il | 100,000 | 9 | 54.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 100,000 | 5 | 61 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe300-il | 200,000 | 9 | 79.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 200,000 | 5 | 81.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe300-il | 500,000 | 9 | 107.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 500,000 | 5 | 105.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe300-il | 1,000,000 | 9 | 130.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 1,000,000 | 5 | 126.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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