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 | ||
(fx66a175-il) WORTMANN FX 66-17A-175 AIRFOIL | Wortmann FX 66-17A-175 airfoil Max thickness 17.5% at 33.9% chord Max camber 4.2% at 40.2% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx66a175-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66a175-il | 50,000 | 9 | 4.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 50,000 | 5 | 12.3 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 100,000 | 9 | 12.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 100,000 | 5 | 34.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 200,000 | 9 | 70.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 200,000 | 5 | 71.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 500,000 | 9 | 103.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 500,000 | 5 | 100.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66a175-il | 1,000,000 | 9 | 128.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66a175-il | 1,000,000 | 5 | 124.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||