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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(goe459-il) GOE 459 AIRFOIL | Gottingen 459 airfoil Max thickness 12.7% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe459-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe459-il | 50,000 | 9 | 28.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe459-il | 50,000 | 5 | 27.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe459-il | 100,000 | 9 | 40.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe459-il | 100,000 | 5 | 37.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe459-il | 200,000 | 9 | 49.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe459-il | 200,000 | 5 | 45.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe459-il | 500,000 | 9 | 59 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe459-il | 500,000 | 5 | 60.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe459-il | 1,000,000 | 9 | 75.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe459-il | 1,000,000 | 5 | 75.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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