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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(goe311-il) GOE 311 (MVA H.43) AIRFOIL | Gottingen 311 (MVA H.43) airfoil Max thickness 8.4% at 19.9% chord Max camber 6.1% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe311-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe311-il | 50,000 | 9 | 14.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 50,000 | 5 | 34.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe311-il | 100,000 | 9 | 57.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 100,000 | 5 | 59.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe311-il | 200,000 | 9 | 82.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 200,000 | 5 | 82 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe311-il | 500,000 | 9 | 114 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 500,000 | 5 | 106.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe311-il | 1,000,000 | 9 | 136.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe311-il | 1,000,000 | 5 | 97.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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