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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(dormoy-il) Dormoy | Dormoy airfoil Max thickness 9% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (dormoy-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dormoy-il | 50,000 | 9 | 36.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dormoy-il | 50,000 | 5 | 36.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dormoy-il | 100,000 | 9 | 50.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dormoy-il | 100,000 | 5 | 45.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dormoy-il | 200,000 | 9 | 57.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dormoy-il | 200,000 | 5 | 50.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dormoy-il | 500,000 | 9 | 64.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dormoy-il | 500,000 | 5 | 62.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dormoy-il | 1,000,000 | 9 | 104.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dormoy-il | 1,000,000 | 5 | 75.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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