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 | ||
(fx63145-il) FX 63-145 AIRFOIL | Wortmann FX 63-145 airfoil Max thickness 14.5% at 30.9% chord Max camber 4% at 37.1% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx63145-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63145-il | 50,000 | 9 | 13.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 50,000 | 5 | 33.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63145-il | 100,000 | 9 | 56.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 100,000 | 5 | 56.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63145-il | 200,000 | 9 | 75.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 200,000 | 5 | 59.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63145-il | 500,000 | 9 | 75.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 500,000 | 5 | 72.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63145-il | 1,000,000 | 9 | 86.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 1,000,000 | 5 | 81.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||