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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(goe394-il) GOE 394 AIRFOIL | Gottingen 394 airfoil Max thickness 6.1% at 19.9% chord Max camber 5.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe394-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe394-il | 50,000 | 9 | 40.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 50,000 | 5 | 44.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe394-il | 100,000 | 9 | 64.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 100,000 | 5 | 66.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe394-il | 200,000 | 9 | 90.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 200,000 | 5 | 85.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe394-il | 500,000 | 9 | 116.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 500,000 | 5 | 108 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe394-il | 1,000,000 | 9 | 139.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 1,000,000 | 5 | 112.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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