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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(goe377-il) GOE 377 AIRFOIL | Gottingen 377 airfoil Max thickness 6.5% at 30% chord Max camber 3.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe377-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe377-il | 50,000 | 9 | 37.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe377-il | 50,000 | 5 | 41 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe377-il | 100,000 | 9 | 57.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe377-il | 100,000 | 5 | 58.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe377-il | 200,000 | 9 | 77.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe377-il | 200,000 | 5 | 73.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe377-il | 500,000 | 9 | 101.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe377-il | 500,000 | 5 | 91.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe377-il | 1,000,000 | 9 | 115.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe377-il | 1,000,000 | 5 | 105.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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