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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(m685-il) M6 (85%) | NACA/Munk M6 (85%) Max thickness 10.2% at 30% chord Max camber 1.9% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m685-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m685-il | 50,000 | 9 | 33.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 50,000 | 5 | 34.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 100,000 | 9 | 50.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 100,000 | 5 | 49.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 200,000 | 9 | 66.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 200,000 | 5 | 62.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 500,000 | 9 | 84.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 500,000 | 5 | 70.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 1,000,000 | 9 | 85.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 1,000,000 | 5 | 75.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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