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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(goe416a-il) GOE 416A AIRFOIL | Gottingen 416A airfoil Max thickness 11.7% at 29.5% chord Max camber 1.3% at 59.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe416a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe416a-il | 50,000 | 9 | 31.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 50,000 | 5 | 34 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 100,000 | 9 | 46.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 100,000 | 5 | 47.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 200,000 | 9 | 61.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 200,000 | 5 | 57.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 500,000 | 9 | 71 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 500,000 | 5 | 67.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 1,000,000 | 9 | 80.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 1,000,000 | 5 | 75.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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