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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(goe12k-il) GOE 12K AIRFOIL | Gottingen 12K airfoil Max thickness 11.1% at 50% chord Max camber 4.1% at 60% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe12k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe12k-il | 50,000 | 9 | 28.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 50,000 | 5 | 27.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 100,000 | 9 | 42.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 100,000 | 5 | 40.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 200,000 | 9 | 66.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 200,000 | 5 | 65.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 500,000 | 9 | 114 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 500,000 | 5 | 104.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 1,000,000 | 9 | 146.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 1,000,000 | 5 | 84.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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