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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(naca64206-il) NACA 64-206 | NACA 64-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca644421-il) NACA 64(4)-421 | NACA 64(4)-421 airfoil Max thickness 20.9% at 34.8% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca643418-il) NACA 64(3)-418 | NACA 64(3)-418 airfoil Max thickness 17.9% at 34.8% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca64206-il,naca644421-il,naca643418-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca64206-il | 50,000 | 9 | 23.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64206-il | 50,000 | 5 | 30.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64206-il | 100,000 | 9 | 43.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64206-il | 100,000 | 5 | 41 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64206-il | 200,000 | 9 | 56.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64206-il | 200,000 | 5 | 51.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64206-il | 500,000 | 9 | 72.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64206-il | 500,000 | 5 | 60.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64206-il | 1,000,000 | 9 | 80.8 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64206-il | 1,000,000 | 5 | 68.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 50,000 | 9 | 3.9 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 50,000 | 5 | 11.3 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 100,000 | 9 | 21.9 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 100,000 | 5 | 26.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 200,000 | 9 | 61.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 200,000 | 5 | 62.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 500,000 | 9 | 98.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 500,000 | 5 | 93.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 1,000,000 | 9 | 124.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 1,000,000 | 5 | 112.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643418-il | 50,000 | 9 | 20.8 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643418-il | 50,000 | 5 | 16.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643418-il | 100,000 | 9 | 39.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643418-il | 100,000 | 5 | 42.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643418-il | 200,000 | 9 | 69.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643418-il | 200,000 | 5 | 68.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643418-il | 500,000 | 9 | 101.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643418-il | 500,000 | 5 | 93.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643418-il | 1,000,000 | 9 | 123.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643418-il | 1,000,000 | 5 | 109.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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