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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(goe115-il) GOE 115 (MVA MK.2) AIRFOIL | Gottingen 115 (MVA MK.2) airfoil Max thickness 9.7% at 29.7% chord Max camber 3.7% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe115-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe115-il | 50,000 | 9 | 32.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 50,000 | 5 | 37.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe115-il | 100,000 | 9 | 57.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 100,000 | 5 | 57.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe115-il | 200,000 | 9 | 77.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 200,000 | 5 | 76.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe115-il | 500,000 | 9 | 108.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 500,000 | 5 | 102.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe115-il | 1,000,000 | 9 | 132 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe115-il | 1,000,000 | 5 | 98.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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