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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(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 |
(naca661212-il) NACA 66(1)-212 | NACA 66(1)-212 airfoil Max thickness 12% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca65209-il) NACA 65-209 | NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca651412-il) NACA 65(1)-412 | NACA 65(1)-412 airfoil Max thickness 12% at 39.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca66209-il,naca661212-il,naca65209-il,naca651412-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| naca661212-il | 50,000 | 9 | 22 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 50,000 | 5 | 22.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca661212-il | 100,000 | 9 | 37.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 100,000 | 5 | 32.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca661212-il | 200,000 | 9 | 47.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 200,000 | 5 | 46.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca661212-il | 500,000 | 9 | 71.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 500,000 | 5 | 62.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca661212-il | 1,000,000 | 9 | 86 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 1,000,000 | 5 | 70.5 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65209-il | 50,000 | 9 | 24.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 50,000 | 5 | 30.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65209-il | 100,000 | 9 | 43.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 100,000 | 5 | 42.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65209-il | 200,000 | 9 | 59.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 200,000 | 5 | 50.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65209-il | 500,000 | 9 | 71.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 500,000 | 5 | 61.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65209-il | 1,000,000 | 9 | 80.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 1,000,000 | 5 | 68 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 50,000 | 9 | 28.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 50,000 | 5 | 30.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 100,000 | 9 | 53 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 100,000 | 5 | 51.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 200,000 | 9 | 74.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 200,000 | 5 | 67.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 500,000 | 9 | 98.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 500,000 | 5 | 88.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 1,000,000 | 9 | 116.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 1,000,000 | 5 | 100.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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