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 | ||
(fx76100-il) WORTMANN FX 76-100 | Wortmann FX 76-100 symmetrical airfoil Max thickness 10.1% at 27.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx76100-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx76100-il | 50,000 | 9 | 25.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76100-il | 50,000 | 5 | 26.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76100-il | 100,000 | 9 | 35.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76100-il | 100,000 | 5 | 36.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76100-il | 200,000 | 9 | 47.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76100-il | 200,000 | 5 | 46.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76100-il | 500,000 | 9 | 62.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76100-il | 500,000 | 5 | 61.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76100-il | 1,000,000 | 9 | 75.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76100-il | 1,000,000 | 5 | 75.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||