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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(goe595-il) GOE 595 AIRFOIL | Gottingen 595 airfoil Max thickness 9.6% at 30% chord Max camber 3% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe595-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe595-il | 50,000 | 9 | 36.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 50,000 | 5 | 38.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe595-il | 100,000 | 9 | 55.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 100,000 | 5 | 54.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe595-il | 200,000 | 9 | 74.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 200,000 | 5 | 68.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe595-il | 500,000 | 9 | 97.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 500,000 | 5 | 86.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe595-il | 1,000,000 | 9 | 110.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 1,000,000 | 5 | 100.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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