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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(goe285-il) GOE 285 AIRFOIL | Gottingen 285 airfoil Max thickness 11.7% at 30% chord Max camber 3.7% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe285-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe285-il | 50,000 | 9 | 26.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 50,000 | 5 | 34.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 100,000 | 9 | 47.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 100,000 | 5 | 50.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 200,000 | 9 | 65.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 200,000 | 5 | 65.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 500,000 | 9 | 89.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 500,000 | 5 | 87 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 1,000,000 | 9 | 109.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 1,000,000 | 5 | 103.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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