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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(goe380-il) GOE 380 AIRFOIL | Gottingen 380 airfoil Max thickness 6.6% at 30% chord Max camber 5.6% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe380-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe380-il | 50,000 | 9 | 31.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe380-il | 50,000 | 5 | 40.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe380-il | 100,000 | 9 | 54.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe380-il | 100,000 | 5 | 60 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe380-il | 200,000 | 9 | 75.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe380-il | 200,000 | 5 | 78 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe380-il | 500,000 | 9 | 103.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe380-il | 500,000 | 5 | 103.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe380-il | 1,000,000 | 9 | 125.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe380-il | 1,000,000 | 5 | 124.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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