Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(pw1211-pw) PW1211 | Peter Wick. Airfoil for plank model gliders Max thickness 7% at 24% chord Max camber 1.7% at 28.2% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (pw1211-pw)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pw1211-pw | 50,000 | 9 | 27.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 100,000 | 9 | 41.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 200,000 | 9 | 55.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 500,000 | 9 | 74.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 1,000,000 | 9 | 87.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 2,000,000 | 9 | 99.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 5,000,000 | 9 | 114.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||