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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(naca25112-jf) NACA 25112 | NACA 25112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 2% at 27.2% chord | Remove Airfoil details Airfoil plotter |
(naca2415-il) NACA 2415 | NACA 2415 airfoil Max thickness 15% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca24112-jf) NACA 24112 | NACA 24112 5 digit reflex airfoil Max thickness 12% at 29.4% chord Max camber 1.7% at 20.6% chord | Remove Airfoil details Airfoil plotter |
(naca2412-il) NACA 2412 | NACA 2412 airfoil Max thickness 12% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca63206-il) NACA 63-206 | NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca25112-jf,naca2415-il,naca24112-jf,naca2412-il,naca63206-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca25112-jf | 50,000 | 9 | 17.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 50,000 | 5 | 28.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca25112-jf | 100,000 | 9 | 42.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 100,000 | 5 | 46.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca25112-jf | 200,000 | 9 | 62.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 200,000 | 5 | 63.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca25112-jf | 500,000 | 9 | 89.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 500,000 | 5 | 85.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca25112-jf | 1,000,000 | 9 | 109.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 1,000,000 | 5 | 98.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2415-il | 50,000 | 9 | 27.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 50,000 | 5 | 31.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2415-il | 100,000 | 9 | 46.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 100,000 | 5 | 47.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2415-il | 200,000 | 9 | 64.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 200,000 | 5 | 61.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2415-il | 500,000 | 9 | 86.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 500,000 | 5 | 79.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2415-il | 1,000,000 | 9 | 102.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 1,000,000 | 5 | 88.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca24112-jf | 50,000 | 9 | 19.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 50,000 | 5 | 27.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca24112-jf | 100,000 | 9 | 37.3 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 100,000 | 5 | 43.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca24112-jf | 200,000 | 9 | 57.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 200,000 | 5 | 60.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca24112-jf | 500,000 | 9 | 84.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 500,000 | 5 | 83 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca24112-jf | 1,000,000 | 9 | 105.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca24112-jf | 1,000,000 | 5 | 98.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 50,000 | 9 | 32.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 50,000 | 5 | 34.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 100,000 | 9 | 50 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 100,000 | 5 | 49.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 200,000 | 9 | 66.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 200,000 | 5 | 62.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 500,000 | 9 | 87.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 500,000 | 5 | 78.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2412-il | 1,000,000 | 9 | 101.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2412-il | 1,000,000 | 5 | 87 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 50,000 | 9 | 24.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 50,000 | 5 | 31.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 100,000 | 9 | 43.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 100,000 | 5 | 41.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 200,000 | 9 | 57 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 200,000 | 5 | 52.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 500,000 | 9 | 72.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 500,000 | 5 | 58.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 1,000,000 | 9 | 80.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 1,000,000 | 5 | 69 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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