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 | ||
(fx63143-il) FX 63-143 AIRFOIL | Wortmann FX 63-143 airfoil Max thickness 14.3% at 33.9% chord Max camber 3.1% at 30.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx63143-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63143-il | 50,000 | 9 | 10.7 at α=-1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 50,000 | 5 | 24 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 100,000 | 9 | 46.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 100,000 | 5 | 49.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 200,000 | 9 | 72.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 200,000 | 5 | 65.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 500,000 | 9 | 71 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 500,000 | 5 | 64.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 1,000,000 | 9 | 79.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 1,000,000 | 5 | 78.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||