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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(goe494-il) GOE 494 AIRFOIL | Gottingen 494 airfoil Max thickness 5% at 20% chord Max camber 5.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe494-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe494-il | 50,000 | 9 | 44.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 50,000 | 5 | 45.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 100,000 | 9 | 69.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 100,000 | 5 | 69.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 200,000 | 9 | 97 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 200,000 | 5 | 95.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 500,000 | 9 | 135.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 500,000 | 5 | 121.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 1,000,000 | 9 | 164.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 1,000,000 | 5 | 112.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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