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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(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 (naca25112-jf)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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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