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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(n64212ma-il) NACA 64(1)-212 MOD A | NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil Max thickness 12% at 41.2% chord Max camber 2.5% at 21.5% chord | Remove Airfoil details Airfoil plotter |
(mh62-il) MH 62 9.3% | Martin Hepperle MH 62 for flying wings Max thickness 9.3% at 26.9% chord Max camber 1.6% at 36.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n64212ma-il,mh62-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64212ma-il | 50,000 | 9 | 29.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 50,000 | 5 | 28.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212ma-il | 100,000 | 9 | 42.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 100,000 | 5 | 38.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212ma-il | 200,000 | 9 | 49.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 200,000 | 5 | 48.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212ma-il | 500,000 | 9 | 68.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 500,000 | 5 | 68.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212ma-il | 1,000,000 | 9 | 83.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212ma-il | 1,000,000 | 5 | 79.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 50,000 | 9 | 28.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 50,000 | 5 | 33.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 100,000 | 9 | 45 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 100,000 | 5 | 46 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 200,000 | 9 | 60.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 200,000 | 5 | 58.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 500,000 | 9 | 80.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 500,000 | 5 | 75 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 1,000,000 | 9 | 94.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 1,000,000 | 5 | 87.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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