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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(goe587-il) GOE 587 AIRFOIL | Gottingen 587 airfoil Max thickness 5.8% at 40% chord Max camber 3% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe587-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe587-il | 50,000 | 9 | 36.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 50,000 | 5 | 37 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 100,000 | 9 | 50.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 100,000 | 5 | 50.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 200,000 | 9 | 63.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 200,000 | 5 | 62.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 500,000 | 9 | 77.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 500,000 | 5 | 70.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 1,000,000 | 9 | 77.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 1,000,000 | 5 | 77.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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