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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(goe140-il) GOE 140 (MVA H.17) AIRFOIL | Gottingen 140 (MVA H.17) airfoil Max thickness 8.8% at 29.9% chord Max camber 5.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe140-il | 50,000 | 9 | 28.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe140-il | 50,000 | 5 | 37.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe140-il | 100,000 | 9 | 54.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe140-il | 100,000 | 5 | 56.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe140-il | 200,000 | 9 | 74.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe140-il | 200,000 | 5 | 74 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe140-il | 500,000 | 9 | 100.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe140-il | 500,000 | 5 | 96.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe140-il | 1,000,000 | 9 | 119.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe140-il | 1,000,000 | 5 | 112 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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