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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(marsden-il) Marsden | Marsden airfoil Max thickness 27.9% at 31.6% chord Max camber 7.7% at 37.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (marsden-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| marsden-il | 50,000 | 9 | 3 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 50,000 | 5 | 3.5 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 100,000 | 9 | 3 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 100,000 | 5 | 4.7 at α=-10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 200,000 | 9 | 5.1 at α=-8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 200,000 | 5 | 17 at α=-2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 500,000 | 9 | 28.7 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 500,000 | 5 | 59.1 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 1,000,000 | 9 | 70.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 1,000,000 | 5 | 98 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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