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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(goe602m-il) GOE 602 MOD. AIRFOIL | Gottingen 602 MOD airfoil Max thickness 9.6% at 30% chord Max camber 3.8% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe602m-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe602m-il | 50,000 | 9 | 39.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 50,000 | 5 | 40.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602m-il | 100,000 | 9 | 59.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 100,000 | 5 | 59.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602m-il | 200,000 | 9 | 80 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 200,000 | 5 | 76.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602m-il | 500,000 | 9 | 105.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 500,000 | 5 | 95.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602m-il | 1,000,000 | 9 | 122.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 1,000,000 | 5 | 108.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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