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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(goe400-il) GOE 400 AIRFOIL | Gottingen 400 airfoil Max thickness 6.1% at 20% chord Max camber 4.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe400-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe400-il | 50,000 | 9 | 37.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 50,000 | 5 | 41.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 100,000 | 9 | 59.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 100,000 | 5 | 61.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 200,000 | 9 | 81 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 200,000 | 5 | 79.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 500,000 | 9 | 109.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 500,000 | 5 | 88.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 1,000,000 | 9 | 126 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 1,000,000 | 5 | 101.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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