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 | ||
(fx05188-il) WORTMANN FX 05-188 AIRFOIL | Wortmann FX 05-188 airfoil Max thickness 18.8% at 37.1% chord Max camber 2.6% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx05188-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx05188-il | 50,000 | 9 | 17.1 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 50,000 | 5 | 14.2 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 100,000 | 9 | 27.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 100,000 | 5 | 29.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 200,000 | 9 | 60.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 200,000 | 5 | 64.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 500,000 | 9 | 99.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 500,000 | 5 | 97.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 1,000,000 | 9 | 126.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 1,000,000 | 5 | 117.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||