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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(naca64a210-il) NACA 64A210 | NACA 64A210 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca64a210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca64a210-il | 50,000 | 9 | 33.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 50,000 | 5 | 32.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a210-il | 100,000 | 9 | 49.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 100,000 | 5 | 46.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a210-il | 200,000 | 9 | 65.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 200,000 | 5 | 59.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a210-il | 500,000 | 9 | 85 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 500,000 | 5 | 68.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a210-il | 1,000,000 | 9 | 93.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 1,000,000 | 5 | 73.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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