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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(goe393-il) GOE 393 AIRFOIL | Gottingen 393 airfoil Max thickness 6.1% at 19.9% chord Max camber 4.2% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe393-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe393-il | 50,000 | 9 | 34.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 50,000 | 5 | 39.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe393-il | 100,000 | 9 | 55.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 100,000 | 5 | 57.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe393-il | 200,000 | 9 | 75.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 200,000 | 5 | 74.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe393-il | 500,000 | 9 | 101.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 500,000 | 5 | 97.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe393-il | 1,000,000 | 9 | 120.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 1,000,000 | 5 | 113.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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