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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(goe116-il) GOE 116 (MVA MK.3) AIRFOIL | Gottingen 116 (MVA MK.3) airfoil Max thickness 9.3% at 39.8% chord Max camber 4.1% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe116-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe116-il | 50,000 | 9 | 29.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 50,000 | 5 | 37.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 100,000 | 9 | 58 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 100,000 | 5 | 56.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 200,000 | 9 | 78.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 200,000 | 5 | 76.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 500,000 | 9 | 106.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 500,000 | 5 | 81.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 1,000,000 | 9 | 100.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 1,000,000 | 5 | 91.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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