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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(goe05k-il) GOE 5K AIRFOIL | Gottingen 5K airfoil Max thickness 3.7% at 50% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe05k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe05k-il | 50,000 | 9 | 20.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 50,000 | 5 | 21.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe05k-il | 100,000 | 9 | 25.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 100,000 | 5 | 27.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe05k-il | 200,000 | 9 | 33.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 200,000 | 5 | 39.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe05k-il | 500,000 | 9 | 71.3 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 500,000 | 5 | 82.4 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe05k-il | 1,000,000 | 9 | 95.1 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe05k-il | 1,000,000 | 5 | 95.1 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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