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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(goe360-il) GOE 360 AIRFOIL | Gottingen 360 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.9% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe360-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe360-il | 50,000 | 9 | 20.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 50,000 | 5 | 36.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe360-il | 100,000 | 9 | 51.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 100,000 | 5 | 56.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe360-il | 200,000 | 9 | 73.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 200,000 | 5 | 76.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe360-il | 500,000 | 9 | 105.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 500,000 | 5 | 104.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe360-il | 1,000,000 | 9 | 131.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe360-il | 1,000,000 | 5 | 127.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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