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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(goe610bm-il) GOE 610-B MOD. AIRFOIL | Gottingen 610-B MOD airfoil Max thickness 7.7% at 30% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe610bm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe610bm-il | 50,000 | 9 | 40.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 50,000 | 5 | 43.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610bm-il | 100,000 | 9 | 62.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 100,000 | 5 | 63.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610bm-il | 200,000 | 9 | 83.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 200,000 | 5 | 82.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610bm-il | 500,000 | 9 | 110.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 500,000 | 5 | 107.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610bm-il | 1,000,000 | 9 | 130.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 1,000,000 | 5 | 125 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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