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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(goe199-il) GOE 199 (L.F.G. 5406) AIRFOIL | Gottingen 199 (L.F.G. 5406) airfoil Max thickness 7.3% at 30% chord Max camber 5.2% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe199-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe199-il | 50,000 | 9 | 36.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 50,000 | 5 | 40.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 100,000 | 9 | 55.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 100,000 | 5 | 54.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 200,000 | 9 | 72 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 200,000 | 5 | 67.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 500,000 | 9 | 89.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 500,000 | 5 | 89.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 1,000,000 | 9 | 108.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 1,000,000 | 5 | 106.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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