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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(goe113-il) GOE 113 AIRFOIL | Gottingen 113 airfoil Max thickness 6.7% at 30% chord Max camber 3% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe113-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe113-il | 50,000 | 9 | 37.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 50,000 | 5 | 40 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe113-il | 100,000 | 9 | 54.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 100,000 | 5 | 54.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe113-il | 200,000 | 9 | 70 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 200,000 | 5 | 66.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe113-il | 500,000 | 9 | 86.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 500,000 | 5 | 78 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe113-il | 1,000,000 | 9 | 97.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 1,000,000 | 5 | 83.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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