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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(nacacyh-il) NACA CYH | NACA CYH airfoil Max thickness 11.7% at 30% chord Max camber 2.8% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca747a315-il) NACA 747A315 | NACA 747A315 airfoil Max thickness 15% at 40.2% chord Max camber 2.5% at 35% chord | Remove Airfoil details Airfoil plotter |
(naca663218-il) NACA 66(3)-218 | NACA 66(3)-218 airfoil Max thickness 18% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nacacyh-il,naca747a315-il,naca663218-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nacacyh-il | 50,000 | 9 | 25.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 50,000 | 5 | 33.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 100,000 | 9 | 47.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 100,000 | 5 | 49.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 200,000 | 9 | 65.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 200,000 | 5 | 64.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 500,000 | 9 | 90.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 500,000 | 5 | 87 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 1,000,000 | 9 | 110.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 1,000,000 | 5 | 101 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 50,000 | 9 | 20.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 50,000 | 5 | 17.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 100,000 | 9 | 44.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 100,000 | 5 | 46.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 200,000 | 9 | 72 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 200,000 | 5 | 61.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 500,000 | 9 | 89.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 500,000 | 5 | 85.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 1,000,000 | 9 | 111.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 1,000,000 | 5 | 100.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663218-il | 50,000 | 9 | 19.3 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 50,000 | 5 | 16.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663218-il | 100,000 | 9 | 26.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 100,000 | 5 | 22.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663218-il | 200,000 | 9 | 38.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 200,000 | 5 | 41.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663218-il | 500,000 | 9 | 76.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 500,000 | 5 | 72.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca663218-il | 1,000,000 | 9 | 99.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca663218-il | 1,000,000 | 5 | 87.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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