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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(naca2410-il) NACA 2410 | NACA 2410 airfoil Max thickness 10% at 29.9% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(ncambre-il) ONERA NACA CAMBRE AIRFOIL | ONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil Max thickness 11.5% at 31.2% chord Max camber 1.4% at 15.9% chord | Remove Airfoil details Airfoil plotter |
(naca64a210-il) NACA 64A210 | NACA 64A210 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(n6h10-il) NACA 6-H-10 AIRFOIL | NACA 6-H-10 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 4.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(n8h12-il) NACA 8-H-12 AIRFOIL | NACA 8-H-12 rotorcraft airfoil Max thickness 12% at 30% chord Max camber 3.5% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca2410-il,ncambre-il,naca64a210-il,n6h10-il,n8h12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2410-il | 50,000 | 9 | 35.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 50,000 | 5 | 36.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 100,000 | 9 | 51.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 100,000 | 5 | 49.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 200,000 | 9 | 67.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 200,000 | 5 | 62 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 500,000 | 9 | 86.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 500,000 | 5 | 75.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 1,000,000 | 9 | 98.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 1,000,000 | 5 | 83.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 50,000 | 9 | 26.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 50,000 | 5 | 29.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 100,000 | 9 | 39.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 100,000 | 5 | 41.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 200,000 | 9 | 52.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 200,000 | 5 | 54.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 500,000 | 9 | 73.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 500,000 | 5 | 73 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 1,000,000 | 9 | 90.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 1,000,000 | 5 | 88 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a210-il | 50,000 | 9 | 33.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 50,000 | 5 | 32.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a210-il | 100,000 | 9 | 49.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 100,000 | 5 | 46.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a210-il | 200,000 | 9 | 65.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 200,000 | 5 | 59.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a210-il | 500,000 | 9 | 85 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 500,000 | 5 | 68.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a210-il | 1,000,000 | 9 | 93.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a210-il | 1,000,000 | 5 | 73.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h10-il | 50,000 | 9 | 23.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 50,000 | 5 | 17.7 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h10-il | 100,000 | 9 | 48.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 100,000 | 5 | 44.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h10-il | 200,000 | 9 | 71.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 200,000 | 5 | 68.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h10-il | 500,000 | 9 | 87 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 500,000 | 5 | 87.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h10-il | 1,000,000 | 9 | 107.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h10-il | 1,000,000 | 5 | 99.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n8h12-il | 50,000 | 9 | 8 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 50,000 | 5 | 18.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n8h12-il | 100,000 | 9 | 45.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 100,000 | 5 | 48 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n8h12-il | 200,000 | 9 | 72 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 200,000 | 5 | 71.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n8h12-il | 500,000 | 9 | 104.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 500,000 | 5 | 98.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n8h12-il | 1,000,000 | 9 | 128.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 1,000,000 | 5 | 118.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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