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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(goe488-il) GOE 488 AIRFOIL | Gottingen 488 airfoil Max thickness 6.8% at 19.9% chord Max camber 3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe488-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe488-il | 50,000 | 9 | 37.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe488-il | 50,000 | 5 | 37.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe488-il | 100,000 | 9 | 55.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe488-il | 100,000 | 5 | 51.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe488-il | 200,000 | 9 | 74.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe488-il | 200,000 | 5 | 64.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe488-il | 500,000 | 9 | 96.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe488-il | 500,000 | 5 | 79.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe488-il | 1,000,000 | 9 | 101.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe488-il | 1,000,000 | 5 | 89.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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