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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(naca64a410-il) NACA 64A410 | NACA 64A410 airfoil Max thickness 10% at 39.9% chord Max camber 2.7% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca64a410-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca64a410-il | 50,000 | 9 | 38.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 50,000 | 5 | 37.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 100,000 | 9 | 58.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 100,000 | 5 | 55.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 200,000 | 9 | 79 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 200,000 | 5 | 71.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 500,000 | 9 | 100.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 500,000 | 5 | 75.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 1,000,000 | 9 | 98.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 1,000,000 | 5 | 80.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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