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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(goe675-il) GOE 675 AIRFOIL | Gottingen 675 airfoil Max thickness 14.9% at 29.5% chord Max camber 5.9% at 39.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe675-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe675-il | 50,000 | 9 | 8.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 50,000 | 5 | 28.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 100,000 | 9 | 51.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 100,000 | 5 | 52.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 200,000 | 9 | 75.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 200,000 | 5 | 69.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 500,000 | 9 | 104.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 500,000 | 5 | 90.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 1,000,000 | 9 | 117.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 1,000,000 | 5 | 111.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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