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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(goe610b-il) GOE 610 B AIRFOIL | Gottingen 610 B airfoil Max thickness 7.8% at 39.9% chord Max camber 5.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe610b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe610b-il | 50,000 | 9 | 37.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610b-il | 50,000 | 5 | 38.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610b-il | 100,000 | 9 | 61.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610b-il | 100,000 | 5 | 62.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610b-il | 200,000 | 9 | 86.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610b-il | 200,000 | 5 | 84 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610b-il | 500,000 | 9 | 118 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610b-il | 500,000 | 5 | 95.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610b-il | 1,000,000 | 9 | 132.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610b-il | 1,000,000 | 5 | 99.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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