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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(goe397-il) GOE 397 AIRFOIL | Gottingen 397 airfoil Max thickness 5.1% at 30% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe397-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe397-il | 50,000 | 9 | 42.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe397-il | 50,000 | 5 | 43 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe397-il | 100,000 | 9 | 61.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe397-il | 100,000 | 5 | 61 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe397-il | 200,000 | 9 | 81.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe397-il | 200,000 | 5 | 79.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe397-il | 500,000 | 9 | 110 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe397-il | 500,000 | 5 | 102.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe397-il | 1,000,000 | 9 | 129.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe397-il | 1,000,000 | 5 | 97.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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