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 | ||
(fx76mp120-il) FX 76-MP-120 | Wortmann FX 76-MP-120 airfoil Max thickness 12.1% at 33.9% chord Max camber 7.6% at 46.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx76mp120-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx76mp120-il | 50,000 | 9 | 6.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 50,000 | 5 | 16.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp120-il | 100,000 | 9 | 42.9 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 100,000 | 5 | 41.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp120-il | 200,000 | 9 | 85.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 200,000 | 5 | 88.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp120-il | 500,000 | 9 | 147.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 500,000 | 5 | 141.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp120-il | 1,000,000 | 9 | 192.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 1,000,000 | 5 | 174 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||