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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(goe701-il) GOE 701 AIRFOIL | Gottingen 701 airfoil Max thickness 12.5% at 29.6% chord Max camber 4.9% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe701-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe701-il | 50,000 | 9 | 19.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 50,000 | 5 | 31.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe701-il | 100,000 | 9 | 54.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 100,000 | 5 | 53.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe701-il | 200,000 | 9 | 78.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 200,000 | 5 | 73.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe701-il | 500,000 | 9 | 108.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 500,000 | 5 | 94.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe701-il | 1,000,000 | 9 | 127.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 1,000,000 | 5 | 101.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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