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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(goe233-il) GOE 233 (MVA CA4) AIRFOIL | Gottingen 233 (MVA CA4) airfoil Max thickness 11.6% at 19.8% chord Max camber 8.2% at 49.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe233-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe233-il | 50,000 | 9 | 26.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 50,000 | 5 | 33.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe233-il | 100,000 | 9 | 60.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 100,000 | 5 | 63.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe233-il | 200,000 | 9 | 86.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 200,000 | 5 | 87.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe233-il | 500,000 | 9 | 120.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 500,000 | 5 | 115.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe233-il | 1,000,000 | 9 | 146.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 1,000,000 | 5 | 134.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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