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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(waspsm-il) WASP (smoothed) | Mike Fox WASP low Reynolds number airfoil Max thickness 9.4% at 27.1% chord Max camber 3% at 37.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (waspsm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| waspsm-il | 50,000 | 9 | 31.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 50,000 | 5 | 37.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| waspsm-il | 100,000 | 9 | 51 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 100,000 | 5 | 53.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| waspsm-il | 200,000 | 9 | 69.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 200,000 | 5 | 69.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| waspsm-il | 500,000 | 9 | 96 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 500,000 | 5 | 91 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| waspsm-il | 1,000,000 | 9 | 115.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| waspsm-il | 1,000,000 | 5 | 108.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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