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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(goe165-il) GOE 165 (MVA MK.11) AIRFOIL | Gottingen 165 (MVA MK.11) airfoil Max thickness 12.1% at 19.7% chord Max camber 5.7% at 49.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe165-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe165-il | 50,000 | 9 | 31.3 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe165-il | 50,000 | 5 | 39.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe165-il | 100,000 | 9 | 54.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe165-il | 100,000 | 5 | 53.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe165-il | 200,000 | 9 | 69.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe165-il | 200,000 | 5 | 66.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe165-il | 500,000 | 9 | 85.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe165-il | 500,000 | 5 | 79.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe165-il | 1,000,000 | 9 | 96.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe165-il | 1,000,000 | 5 | 85.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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