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 | ||
(fx74cl6140-il) FX 74-CL6-140 | Wortmann FX 74-CL6-140 airfoil Max thickness 14.1% at 30.9% chord Max camber 7.1% at 33.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx74cl6140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74cl6140-il | 50,000 | 9 | 5.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 50,000 | 5 | 18.9 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 100,000 | 9 | 19.9 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 100,000 | 5 | 40.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 200,000 | 9 | 48.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 200,000 | 5 | 72 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 500,000 | 9 | 114.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 500,000 | 5 | 120.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 1,000,000 | 9 | 157.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 1,000,000 | 5 | 158.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||