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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(goe198-il) GOE 198 (L.F.G. 5294) AIRFOIL | Gottingen 198 (L.F.G. 5294) airfoil Max thickness 7.8% at 19.9% chord Max camber 6.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe198-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe198-il | 50,000 | 9 | 36.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 50,000 | 5 | 43.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe198-il | 100,000 | 9 | 64.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 100,000 | 5 | 64 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe198-il | 200,000 | 9 | 88.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 200,000 | 5 | 80.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe198-il | 500,000 | 9 | 112.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 500,000 | 5 | 92.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe198-il | 1,000,000 | 9 | 117 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 1,000,000 | 5 | 92.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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