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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(goe358-il) GOE 358 AIRFOIL | Gottingen 358 airfoil Max thickness 10.9% at 20% chord Max camber 5.6% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe358-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe358-il | 50,000 | 9 | 37.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 50,000 | 5 | 42.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 9 | 58.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 5 | 61.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 9 | 79 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 5 | 79 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 9 | 105.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 5 | 99.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 9 | 119.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 5 | 115.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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