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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(goe381-il) GOE 381 AIRFOIL | Gottingen 381 airfoil Max thickness 6.4% at 30% chord Max camber 5.8% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe381-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe381-il | 50,000 | 9 | 37.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 50,000 | 5 | 43 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe381-il | 100,000 | 9 | 58.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 100,000 | 5 | 61.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe381-il | 200,000 | 9 | 80 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 200,000 | 5 | 76.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe381-il | 500,000 | 9 | 100.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 500,000 | 5 | 92 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe381-il | 1,000,000 | 9 | 111.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe381-il | 1,000,000 | 5 | 93.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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