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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(goe796-il) GOE 796 AIRFOIL | Gottingen 796 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe796-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe796-il | 50,000 | 9 | 32.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 50,000 | 5 | 35.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 100,000 | 9 | 55.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 100,000 | 5 | 55.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 200,000 | 9 | 78 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 200,000 | 5 | 73.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 500,000 | 9 | 105.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 500,000 | 5 | 90.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 1,000,000 | 9 | 122.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 1,000,000 | 5 | 105.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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