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 | ||
(fx79l120-il) FX 79-L-120 | Wortmann FX 79-L-120 symmetrical airfoil Max thickness 12.1% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx79l120-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx79l120-il | 50,000 | 9 | 27.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 50,000 | 5 | 27.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l120-il | 100,000 | 9 | 40.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 100,000 | 5 | 38 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l120-il | 200,000 | 9 | 52.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 200,000 | 5 | 43.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l120-il | 500,000 | 9 | 58.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 500,000 | 5 | 60.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l120-il | 1,000,000 | 9 | 73.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l120-il | 1,000,000 | 5 | 74.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||