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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(goe780-il) GOE 780 AIRFOIL | Gottingen 780 airfoil Max thickness 12% at 50% chord Max camber 1% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe780-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe780-il | 50,000 | 9 | 12.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 50,000 | 5 | 19.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 100,000 | 9 | 29.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 100,000 | 5 | 31.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 200,000 | 9 | 44.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 200,000 | 5 | 34.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 500,000 | 9 | 42.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 500,000 | 5 | 42.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 1,000,000 | 9 | 50.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 1,000,000 | 5 | 44 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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