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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(naca2421-il) NACA 2421 | NACA 2421 airfoil Max thickness 21% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca64210-il) NACA 64-210 | NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca2421-il,naca64210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2421-il | 50,000 | 9 | 6.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2421-il | 50,000 | 5 | 23.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2421-il | 100,000 | 9 | 39.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2421-il | 100,000 | 5 | 41.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2421-il | 200,000 | 9 | 57.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2421-il | 200,000 | 5 | 53.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2421-il | 500,000 | 9 | 75.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2421-il | 500,000 | 5 | 67.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2421-il | 1,000,000 | 9 | 89.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2421-il | 1,000,000 | 5 | 81.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 50,000 | 9 | 30.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 50,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 100,000 | 9 | 46.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 100,000 | 5 | 44.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 200,000 | 9 | 61.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 200,000 | 5 | 54 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 500,000 | 9 | 76.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 500,000 | 5 | 63.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 1,000,000 | 9 | 85.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 1,000,000 | 5 | 72.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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