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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(m26-il) NACA M26 AIRFOIL | NACA/Munk M-26 airfoil Max thickness 8.3% at 40% chord Max camber 8.3% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m26-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m26-il | 50,000 | 9 | 6.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 50,000 | 5 | 14 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 100,000 | 9 | 16.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 100,000 | 5 | 41.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 200,000 | 9 | 78.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 200,000 | 5 | 78.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 500,000 | 9 | 115.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 500,000 | 5 | 98.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 1,000,000 | 9 | 141.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 1,000,000 | 5 | 113.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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