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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(goe434-il) GOE 434 AIRFOIL | Gottingen 434 airfoil Max thickness 22.8% at 28.4% chord Max camber 5.2% at 48.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe434-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe434-il | 50,000 | 9 | 3.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 50,000 | 5 | 11.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe434-il | 100,000 | 9 | 36 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 100,000 | 5 | 36.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe434-il | 200,000 | 9 | 65.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 200,000 | 5 | 62.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe434-il | 500,000 | 9 | 94.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 500,000 | 5 | 83.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe434-il | 1,000,000 | 9 | 110.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 1,000,000 | 5 | 93.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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