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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(goe765-il) Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 | Used on the Me163 Komet Max thickness 14.4% at 30% chord Max camber 1.9% at 25.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe765-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe765-il | 50,000 | 9 | 15.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 50,000 | 5 | 28.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 100,000 | 9 | 41.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 100,000 | 5 | 44.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 200,000 | 9 | 59.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 200,000 | 5 | 58.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 500,000 | 9 | 80.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 500,000 | 5 | 68.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 1,000,000 | 9 | 85.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 1,000,000 | 5 | 79.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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