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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(goe440-il) GOE 440 AIRFOIL | Gottingen 440 airfoil Max thickness 15.3% at 30% chord Max camber 9.7% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe440-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe440-il | 50,000 | 9 | 9.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 50,000 | 5 | 31.9 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 100,000 | 9 | 53.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 100,000 | 5 | 52.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 200,000 | 9 | 71.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 200,000 | 5 | 67.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 500,000 | 9 | 92.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 500,000 | 5 | 86.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 1,000,000 | 9 | 109.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 1,000,000 | 5 | 100.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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