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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(goe195-il) GOE 195 AIRFOIL | Gottingen 195 airfoil Max thickness 8.6% at 20% chord Max camber 5.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe195-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe195-il | 50,000 | 9 | 40.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe195-il | 50,000 | 5 | 44 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe195-il | 100,000 | 9 | 63.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe195-il | 100,000 | 5 | 64.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe195-il | 200,000 | 9 | 86 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe195-il | 200,000 | 5 | 84 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe195-il | 500,000 | 9 | 116.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe195-il | 500,000 | 5 | 109.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe195-il | 1,000,000 | 9 | 139 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe195-il | 1,000,000 | 5 | 106.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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