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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(eiffel430-il) Eiffel 430 (Lachassgne) | Eiffel 430 (Lachassgne) airfoil Max thickness 9.7% at 15% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (eiffel430-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eiffel430-il | 50,000 | 9 | 36.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel430-il | 50,000 | 5 | 32.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel430-il | 100,000 | 9 | 47.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel430-il | 100,000 | 5 | 43.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel430-il | 200,000 | 9 | 58 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel430-il | 200,000 | 5 | 58.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel430-il | 500,000 | 9 | 84.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel430-il | 500,000 | 5 | 71.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel430-il | 1,000,000 | 9 | 92.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel430-il | 1,000,000 | 5 | 85.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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