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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(naca63a210-il) NACA 63A210 | NACA 63A210 airfoil Max thickness 10% at 34.9% chord Max camber 1.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca633018-il) NACA 63(3)-018 | NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca1410-il) NACA 1410 | NACA 1410 airfoil Max thickness 10% at 29.9% chord Max camber 1% at 50% chord | Remove Airfoil details Airfoil plotter |
(n6h15-il) NACA 6-H-15 AIRFOIL | NACA 6-H-15 rotorcraft airfoil Max thickness 15.6% at 40% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca63a210-il,naca633018-il,naca1410-il,n6h15-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca63a210-il | 50,000 | 9 | 28.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 50,000 | 5 | 31.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 100,000 | 9 | 37.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 100,000 | 5 | 40.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 200,000 | 9 | 44.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 200,000 | 5 | 48.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 500,000 | 9 | 52 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 500,000 | 5 | 58.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63a210-il | 1,000,000 | 9 | 58.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63a210-il | 1,000,000 | 5 | 70.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 50,000 | 9 | 23.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 50,000 | 5 | 20.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 9 | 40.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 5 | 36.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 9 | 53.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 5 | 50.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 5 | 61.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 9 | 83 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 5 | 65.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1410-il | 50,000 | 9 | 31.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 50,000 | 5 | 31.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1410-il | 100,000 | 9 | 44.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 100,000 | 5 | 42.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1410-il | 200,000 | 9 | 56.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 200,000 | 5 | 50.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1410-il | 500,000 | 9 | 70.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 500,000 | 5 | 63.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1410-il | 1,000,000 | 9 | 78.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 1,000,000 | 5 | 78.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h15-il | 50,000 | 9 | 15.5 at α=14.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 50,000 | 5 | 10.7 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h15-il | 100,000 | 9 | 17.3 at α=15° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 100,000 | 5 | 23.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h15-il | 200,000 | 9 | 64.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 200,000 | 5 | 53.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h15-il | 500,000 | 9 | 85.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 500,000 | 5 | 83 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h15-il | 1,000,000 | 9 | 109.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 1,000,000 | 5 | 97.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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