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 | ||
(fx71089a-il) WORTMANN FX 71-089A AIRFOIL | Wortmann FX 71-089A airfoil Max thickness 8.9% at 22.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx71089a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx71089a-il | 50,000 | 9 | 19.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 50,000 | 5 | 19.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 100,000 | 9 | 25.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 100,000 | 5 | 26.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 200,000 | 9 | 31.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 200,000 | 5 | 36.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 500,000 | 9 | 46.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 500,000 | 5 | 52.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 1,000,000 | 9 | 59.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 1,000,000 | 5 | 68 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||