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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(goe290-il) GOE 290 (MVA 290) AIRFOIL | Gottingen 290 (MVA 290) airfoil Max thickness 17.6% at 29.1% chord Max camber 3.9% at 39.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe290-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe290-il | 50,000 | 9 | 6.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 50,000 | 5 | 22.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 100,000 | 9 | 41.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 100,000 | 5 | 46.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 200,000 | 9 | 69 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 200,000 | 5 | 67 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 500,000 | 9 | 96.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 500,000 | 5 | 84 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 1,000,000 | 9 | 112.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 1,000,000 | 5 | 92.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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