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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(goe593-il) GOE 593 AIRFOIL | Gottingen 593 airfoil Max thickness 11.9% at 30% chord Max camber 4.1% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe593-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe593-il | 50,000 | 9 | 24.3 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe593-il | 50,000 | 5 | 35.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe593-il | 100,000 | 9 | 52.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe593-il | 100,000 | 5 | 53.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe593-il | 200,000 | 9 | 74.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe593-il | 200,000 | 5 | 69.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe593-il | 500,000 | 9 | 101.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe593-il | 500,000 | 5 | 88.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe593-il | 1,000,000 | 9 | 117.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe593-il | 1,000,000 | 5 | 107.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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