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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(eiffel10-il) Eiffel 10 (Wright) - 1903 Wright Flyer airfoil | Eiffel 10 (Wright) - 1903 Wright Flyer airfoil Max thickness 2.7% at 0% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (eiffel10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eiffel10-il | 50,000 | 9 | 25.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 50,000 | 5 | 27 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel10-il | 100,000 | 9 | 27.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 100,000 | 5 | 29.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel10-il | 200,000 | 9 | 28.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 200,000 | 5 | 34.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel10-il | 500,000 | 9 | 32.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 500,000 | 5 | 38.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel10-il | 1,000,000 | 9 | 36.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel10-il | 1,000,000 | 5 | 45.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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