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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(goe596-il) GOE 596 AIRFOIL | Gottingen 596 airfoil Max thickness 9.8% at 30% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe596-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe596-il | 50,000 | 9 | 35.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 50,000 | 5 | 37 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 100,000 | 9 | 56.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 100,000 | 5 | 57.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 200,000 | 9 | 77.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 200,000 | 5 | 75.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 500,000 | 9 | 105.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 500,000 | 5 | 97.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 1,000,000 | 9 | 125.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 1,000,000 | 5 | 112.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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