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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(goe282-il) GOE 282 (DAIMLER XIII) AIRFOIL | Gottingen 282 (DAIMLER XIII) airfoil Max thickness 9.1% at 19.9% chord Max camber 5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe282-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe282-il | 50,000 | 9 | 34.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe282-il | 50,000 | 5 | 41 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe282-il | 100,000 | 9 | 57 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe282-il | 100,000 | 5 | 59 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe282-il | 200,000 | 9 | 77.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe282-il | 200,000 | 5 | 75.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe282-il | 500,000 | 9 | 102.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe282-il | 500,000 | 5 | 94.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe282-il | 1,000,000 | 9 | 118.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe282-il | 1,000,000 | 5 | 105.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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