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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(goe387-il) GOE 387 AIRFOIL | Gottingen 387 airfoil Max thickness 14.9% at 30% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe387-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe387-il | 50,000 | 9 | 6.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 50,000 | 5 | 22.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe387-il | 100,000 | 9 | 43.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 100,000 | 5 | 50.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe387-il | 200,000 | 9 | 71.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 200,000 | 5 | 69.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe387-il | 500,000 | 9 | 101 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 500,000 | 5 | 93 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe387-il | 1,000,000 | 9 | 122.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe387-il | 1,000,000 | 5 | 114.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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