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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(naca653218-il) NACA 65(3)-218 | NACA 65(3)-218 airfoil Max thickness 18% at 39.9% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca64a410-il) NACA 64A410 | NACA 64A410 airfoil Max thickness 10% at 39.9% chord Max camber 2.7% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca66209-il) NACA 66-209 | NACA 66-209 airfoil Max thickness 9% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca0018-il) NACA 0018 | NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca1412-il) NACA 1412 | NACA 1412 airfoil Max thickness 12% at 29.9% chord Max camber 1% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca653218-il,naca64a410-il,naca66209-il,naca0018-il,naca1412-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca653218-il | 50,000 | 9 | 19.6 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653218-il | 50,000 | 5 | 17.1 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653218-il | 100,000 | 9 | 35.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653218-il | 100,000 | 5 | 31.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653218-il | 200,000 | 9 | 57.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653218-il | 200,000 | 5 | 56.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653218-il | 500,000 | 9 | 85.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653218-il | 500,000 | 5 | 76.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653218-il | 1,000,000 | 9 | 102.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653218-il | 1,000,000 | 5 | 86.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 50,000 | 9 | 38.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 50,000 | 5 | 37.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 100,000 | 9 | 58.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 100,000 | 5 | 55.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 200,000 | 9 | 79 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 200,000 | 5 | 71.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 500,000 | 9 | 100.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 500,000 | 5 | 75.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a410-il | 1,000,000 | 9 | 98.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a410-il | 1,000,000 | 5 | 80.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66209-il | 50,000 | 9 | 22.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 50,000 | 5 | 25.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66209-il | 100,000 | 9 | 32.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 100,000 | 5 | 40.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66209-il | 200,000 | 9 | 53.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 200,000 | 5 | 47.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66209-il | 500,000 | 9 | 67.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 500,000 | 5 | 60.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66209-il | 1,000,000 | 9 | 80.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 1,000,000 | 5 | 64.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 50,000 | 9 | 22.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 50,000 | 5 | 26.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 9 | 37.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 5 | 38.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 9 | 50.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 5 | 48 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 9 | 65.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 5 | 61.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 9 | 77.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 5 | 73.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 50,000 | 9 | 29.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 50,000 | 5 | 31.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 100,000 | 9 | 44.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 100,000 | 5 | 43 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 200,000 | 9 | 57.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 200,000 | 5 | 53.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 500,000 | 9 | 73.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 500,000 | 5 | 66 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 1,000,000 | 9 | 83.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 1,000,000 | 5 | 78.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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