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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(pw51-pw) PW51 | Peter Wick. Airfoil for plank model gliders Max thickness 8.9% at 27.5% chord Max camber 1.4% at 27.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (pw51-pw)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pw51-pw | 50,000 | 9 | 26.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 100,000 | 9 | 41.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 200,000 | 9 | 56.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 500,000 | 9 | 76.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 1,000,000 | 9 | 90.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 2,000,000 | 9 | 104.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 5,000,000 | 9 | 119.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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