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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(goe118-il) GOE 118 (MVA MK.7) AIRFOIL | Gottingen 118 (MVA MK.7) airfoil Max thickness 8.6% at 29.9% chord Max camber 5.7% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe118-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe118-il | 50,000 | 9 | 24.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 50,000 | 5 | 40.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe118-il | 100,000 | 9 | 62 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 100,000 | 5 | 61.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe118-il | 200,000 | 9 | 83.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 200,000 | 5 | 82.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe118-il | 500,000 | 9 | 112.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 500,000 | 5 | 108.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe118-il | 1,000,000 | 9 | 134.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 1,000,000 | 5 | 120.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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