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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(goe133-il) GOE 133 (MVA H.11) AIRFOIL | Gottingen 133 (MVA H.11) airfoil Max thickness 7.9% at 30% chord Max camber 4.3% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe133-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe133-il | 50,000 | 9 | 33.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 50,000 | 5 | 40.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe133-il | 100,000 | 9 | 53.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 100,000 | 5 | 58.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe133-il | 200,000 | 9 | 74.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 200,000 | 5 | 74.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe133-il | 500,000 | 9 | 99.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 500,000 | 5 | 93 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe133-il | 1,000,000 | 9 | 114.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 1,000,000 | 5 | 108 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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