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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(goe574-il) GOE 574 AIRFOIL | Gottingen 574 airfoil Max thickness 10.3% at 30% chord Max camber 4.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe574-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe574-il | 50,000 | 9 | 34.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 50,000 | 5 | 35.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe574-il | 100,000 | 9 | 56 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 100,000 | 5 | 55.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe574-il | 200,000 | 9 | 74.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 200,000 | 5 | 73.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe574-il | 500,000 | 9 | 100 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 500,000 | 5 | 97.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe574-il | 1,000,000 | 9 | 121.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe574-il | 1,000,000 | 5 | 118.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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