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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(goe615-il) GOE 615 AIRFOIL | Gottingen 615 airfoil Max thickness 13.7% at 29.7% chord Max camber 5.6% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe615-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe615-il | 50,000 | 9 | 10.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 50,000 | 5 | 30.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 100,000 | 9 | 51 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 100,000 | 5 | 53 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 200,000 | 9 | 74.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 200,000 | 5 | 72.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 500,000 | 9 | 104.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 500,000 | 5 | 93.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 1,000,000 | 9 | 125.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 1,000,000 | 5 | 102.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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