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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(goe182-il) GOE 182 (MVA H.27) AIRFOIL | Gottingen 182 (MVA H.27) airfoil Max thickness 9.5% at 19.9% chord Max camber 5.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe182-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe182-il | 50,000 | 9 | 29.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe182-il | 50,000 | 5 | 36.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe182-il | 100,000 | 9 | 48.6 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe182-il | 100,000 | 5 | 51.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe182-il | 200,000 | 9 | 68.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe182-il | 200,000 | 5 | 69.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe182-il | 500,000 | 9 | 98 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe182-il | 500,000 | 5 | 97.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe182-il | 1,000,000 | 9 | 122.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe182-il | 1,000,000 | 5 | 119.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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