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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(goe777-il) GOE 777 AIRFOIL | Gottingen 777 airfoil Max thickness 22% at 30% chord Max camber 5.9% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe777-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe777-il | 50,000 | 9 | 3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 50,000 | 5 | 8.1 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe777-il | 100,000 | 9 | 15.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 100,000 | 5 | 32.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe777-il | 200,000 | 9 | 54.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 200,000 | 5 | 57.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe777-il | 500,000 | 9 | 90.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 500,000 | 5 | 81.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe777-il | 1,000,000 | 9 | 109 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 1,000,000 | 5 | 101.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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