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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(goe655-il) GOE 655 AIRFOIL | Gottingen 655 airfoil Max thickness 13.9% at 30% chord Max camber 4.4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe655-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe655-il | 50,000 | 9 | 16.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 50,000 | 5 | 32.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 100,000 | 9 | 45.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 100,000 | 5 | 49 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 200,000 | 9 | 64.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 200,000 | 5 | 64.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 500,000 | 9 | 91.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 500,000 | 5 | 89.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 1,000,000 | 9 | 115.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 1,000,000 | 5 | 109 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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