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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(mb253515sm-il) MB253515 15.0% smoothed | Mike Bame MB253515 low Reynolds number airfoil Max thickness 15% at 35% chord Max camber 2.5% at 37.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mb253515sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mb253515sm-il | 50,000 | 9 | 7.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 50,000 | 5 | 25.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mb253515sm-il | 100,000 | 9 | 48.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 100,000 | 5 | 49 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mb253515sm-il | 200,000 | 9 | 70 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 200,000 | 5 | 68.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mb253515sm-il | 500,000 | 9 | 92.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 500,000 | 5 | 83.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mb253515sm-il | 1,000,000 | 9 | 105.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 1,000,000 | 5 | 96.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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