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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(goe101-il) GOE 101 AIRFOIL | Gottingen 101 airfoil Max thickness 6.9% at 30% chord Max camber 4% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe101-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe101-il | 50,000 | 9 | 39.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 50,000 | 5 | 41.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 100,000 | 9 | 58.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 100,000 | 5 | 59.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 200,000 | 9 | 77.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 200,000 | 5 | 77.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 500,000 | 9 | 104.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 500,000 | 5 | 100.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 1,000,000 | 9 | 123.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 1,000,000 | 5 | 114.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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