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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(goe303-il) GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL | Gottingen 303 (Friedrichshafen G03) airfoil Max thickness 9.8% at 29.9% chord Max camber 5.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe303-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe303-il | 50,000 | 9 | 26.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe303-il | 50,000 | 5 | 39.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe303-il | 100,000 | 9 | 58.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe303-il | 100,000 | 5 | 61.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe303-il | 200,000 | 9 | 83.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe303-il | 200,000 | 5 | 81.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe303-il | 500,000 | 9 | 114.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe303-il | 500,000 | 5 | 106.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe303-il | 1,000,000 | 9 | 137.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe303-il | 1,000,000 | 5 | 122.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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