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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(goe797-il) GOE 797 AIRFOIL | Gottingen 797 airfoil Max thickness 16% at 30% chord Max camber 4.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe797-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe797-il | 50,000 | 9 | 7.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 50,000 | 5 | 20.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe797-il | 100,000 | 9 | 48.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 100,000 | 5 | 50.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe797-il | 200,000 | 9 | 76 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 200,000 | 5 | 73.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe797-il | 500,000 | 9 | 108.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 500,000 | 5 | 96.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe797-il | 1,000,000 | 9 | 128.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe797-il | 1,000,000 | 5 | 106.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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