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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(goe10k-il) GOE 10K AIRFOIL | Gottingen 10K airfoil Max thickness 3.9% at 50% chord Max camber 1.4% at 60% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe10k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe10k-il | 50,000 | 9 | 20.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe10k-il | 50,000 | 5 | 22.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe10k-il | 100,000 | 9 | 27.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe10k-il | 100,000 | 5 | 33.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe10k-il | 200,000 | 9 | 47.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe10k-il | 200,000 | 5 | 56.4 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe10k-il | 500,000 | 9 | 88.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe10k-il | 500,000 | 5 | 74.8 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe10k-il | 1,000,000 | 9 | 111.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe10k-il | 1,000,000 | 5 | 61 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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