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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(naca4415-il) NACA 4415 | NACA 4415 airfoil Max thickness 15% at 30.9% chord Max camber 4% at 40.2% chord | Remove Airfoil details Airfoil plotter |
(naca2418-il) NACA 2418 | NACA 2418 airfoil Max thickness 18% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca632615-il) NACA 63(2)-615 | NACA 63(2)-615 airfoil Max thickness 15% at 34.8% chord Max camber 3.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca4415-il,naca2418-il,naca632615-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca4415-il | 50,000 | 9 | 7.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 50,000 | 5 | 27.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 100,000 | 9 | 48.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 100,000 | 5 | 50.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 200,000 | 9 | 71.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 200,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 500,000 | 9 | 97 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 500,000 | 5 | 90.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 1,000,000 | 9 | 119.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 1,000,000 | 5 | 109.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 50,000 | 9 | 8.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 50,000 | 5 | 27.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 100,000 | 9 | 42.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 100,000 | 5 | 44 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 200,000 | 9 | 60.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 200,000 | 5 | 58.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 500,000 | 9 | 83.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 500,000 | 5 | 75.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 1,000,000 | 9 | 97.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 1,000,000 | 5 | 87.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632615-il | 50,000 | 9 | 27.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632615-il | 50,000 | 5 | 24.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632615-il | 100,000 | 9 | 55 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632615-il | 100,000 | 5 | 55.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632615-il | 200,000 | 9 | 81.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632615-il | 200,000 | 5 | 78.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632615-il | 500,000 | 9 | 112.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632615-il | 500,000 | 5 | 104.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632615-il | 1,000,000 | 9 | 134.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632615-il | 1,000,000 | 5 | 121.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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