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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(goe286-il) GOE 286 AIRFOIL | Gottingen 286 airfoil Max thickness 9.4% at 29.9% chord Max camber 4.1% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe286-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe286-il | 50,000 | 9 | 27.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 50,000 | 5 | 37.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 100,000 | 9 | 52.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 100,000 | 5 | 54.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 200,000 | 9 | 72.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 200,000 | 5 | 65.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 500,000 | 9 | 83.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 500,000 | 5 | 78.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 1,000,000 | 9 | 95.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 1,000,000 | 5 | 89.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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