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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(goe280-il) GOE 280 (DAIMLER XI) AIRFOIL | Gottingen 280 (DAIMLER XI) airfoil Max thickness 7.9% at 30% chord Max camber 4.5% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe280-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe280-il | 50,000 | 9 | 37.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 50,000 | 5 | 41.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 100,000 | 9 | 55.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 100,000 | 5 | 56.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 200,000 | 9 | 72.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 200,000 | 5 | 70.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 500,000 | 9 | 91.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 500,000 | 5 | 79.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 1,000,000 | 9 | 98.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 1,000,000 | 5 | 87.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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