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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(mh22-il) MH 22 7.2% | Martin Hepperle MH 22 for F3D Pylon Racing Max thickness 7.2% at 27% chord Max camber 1.8% at 37% chord | Remove Airfoil details Airfoil plotter |
(naca25112-jf) NACA 25112 | NACA 25112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 2% at 27.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh22-il,naca25112-jf)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh22-il | 50,000 | 9 | 33.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 50,000 | 5 | 35 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 100,000 | 9 | 48.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 100,000 | 5 | 47.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 200,000 | 9 | 63.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 500,000 | 9 | 82.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 500,000 | 5 | 74.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 1,000,000 | 9 | 92.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 1,000,000 | 5 | 81.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca25112-jf | 50,000 | 9 | 17.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 50,000 | 5 | 28.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca25112-jf | 100,000 | 9 | 42.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 100,000 | 5 | 46.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca25112-jf | 200,000 | 9 | 62.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 200,000 | 5 | 63.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca25112-jf | 500,000 | 9 | 89.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 500,000 | 5 | 85.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca25112-jf | 1,000,000 | 9 | 109.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca25112-jf | 1,000,000 | 5 | 98.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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