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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(goe414-il) GOE 414 AIRFOIL | Gottingen 414 airfoil Max thickness 13.6% at 29.7% chord Max camber 5.3% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe414-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe414-il | 50,000 | 9 | 8.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe414-il | 50,000 | 5 | 28.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe414-il | 100,000 | 9 | 52.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe414-il | 100,000 | 5 | 54.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe414-il | 200,000 | 9 | 74.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe414-il | 200,000 | 5 | 73 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe414-il | 500,000 | 9 | 100 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe414-il | 500,000 | 5 | 97 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe414-il | 1,000,000 | 9 | 124.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe414-il | 1,000,000 | 5 | 119 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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