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 | ||
(fx2-il) WORTMANN FX 2 AIRFOIL | Wortmann FX 2 airfoil Max thickness 20.4% at 43.5% chord Max camber 3.8% at 69.1% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx2-il | 50,000 | 9 | 18 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 50,000 | 5 | 14.9 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 100,000 | 9 | 23.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 100,000 | 5 | 22.7 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 200,000 | 9 | 34.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 200,000 | 5 | 34.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 500,000 | 9 | 51.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 500,000 | 5 | 50.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 1,000,000 | 9 | 107.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 1,000,000 | 5 | 111 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||