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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(goe483-il) GOE 483 AIRFOIL | Gottingen 483 airfoil Max thickness 5.5% at 15% chord Max camber 5.8% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe483-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe483-il | 50,000 | 9 | 42.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 50,000 | 5 | 44.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe483-il | 100,000 | 9 | 62.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 100,000 | 5 | 65.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe483-il | 200,000 | 9 | 83.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 200,000 | 5 | 85.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe483-il | 500,000 | 9 | 114.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 500,000 | 5 | 112.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe483-il | 1,000,000 | 9 | 137.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 1,000,000 | 5 | 121.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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