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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(goe177-il) GOE 177 AIRFOIL | Gottingen 177 airfoil Max thickness 7.7% at 20% chord Max camber 5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe177-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe177-il | 50,000 | 9 | 39.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe177-il | 50,000 | 5 | 41.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe177-il | 100,000 | 9 | 58.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe177-il | 100,000 | 5 | 57.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe177-il | 200,000 | 9 | 74.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe177-il | 200,000 | 5 | 71.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe177-il | 500,000 | 9 | 91.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe177-il | 500,000 | 5 | 79.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe177-il | 1,000,000 | 9 | 99.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe177-il | 1,000,000 | 5 | 89.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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