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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(naca23112-jf) NACA 23112 | NACA 23112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 1.2% at 14.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca23112-jf)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca23112-jf | 50,000 | 9 | 22.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23112-jf | 50,000 | 5 | 27.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23112-jf | 100,000 | 9 | 34.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23112-jf | 100,000 | 5 | 39.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23112-jf | 200,000 | 9 | 50.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23112-jf | 200,000 | 5 | 55.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23112-jf | 500,000 | 9 | 77.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23112-jf | 500,000 | 5 | 78.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23112-jf | 1,000,000 | 9 | 98.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23112-jf | 1,000,000 | 5 | 95.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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