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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(goe612-il) GOE 612 AIRFOIL | Gottingen 612 airfoil Max thickness 15% at 29.5% chord Max camber 5% at 49.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe612-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe612-il | 50,000 | 9 | 9.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 50,000 | 5 | 27.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 100,000 | 9 | 51.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 100,000 | 5 | 49.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 200,000 | 5 | 70.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 500,000 | 9 | 105.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 500,000 | 5 | 85.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 1,000,000 | 9 | 121.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 1,000,000 | 5 | 100 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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