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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(goe619-il) GOE 619 AIRFOIL | Gottingen 619 airfoil Max thickness 13.7% at 19.5% chord Max camber 4.5% at 49.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe619-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe619-il | 50,000 | 9 | 22 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 50,000 | 5 | 33.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 100,000 | 9 | 52.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 100,000 | 5 | 51.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 200,000 | 9 | 73.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 200,000 | 5 | 67.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 500,000 | 9 | 99.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 500,000 | 5 | 82 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 1,000,000 | 9 | 108.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 1,000,000 | 5 | 99.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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