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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(goe702-il) GOE 702 AIRFOIL | Gottingen 702 airfoil Max thickness 16.6% at 19.4% chord Max camber 5.1% at 39.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe702-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe702-il | 50,000 | 9 | 4.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 50,000 | 5 | 20.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 100,000 | 9 | 32 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 100,000 | 5 | 43.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 200,000 | 9 | 57.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 200,000 | 5 | 61.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 500,000 | 9 | 88.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 500,000 | 5 | 89.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 1,000,000 | 9 | 117.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 1,000,000 | 5 | 116.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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