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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(goe676-il) GOE 676 (= M 12) AIRFOIL | Gottingen 676 (= M 12) airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe676-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe676-il | 50,000 | 9 | 30.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 50,000 | 5 | 33.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 100,000 | 9 | 48.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 100,000 | 5 | 48.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 200,000 | 9 | 65.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 200,000 | 5 | 62.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 500,000 | 9 | 86.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 500,000 | 5 | 77.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 1,000,000 | 9 | 97.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 1,000,000 | 5 | 85.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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