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 | ||
(fx73170-il) WORTMANN FX 73-170 | Wortmann FX 73-170 airfoil Max thickness 17.1% at 43.5% chord Max camber 4.4% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(fx6617a2-il) FX 66-17AII-182 AIRFOIL | Wortmann FX 66-17AII-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(fx73cl2152-il) FX 73-CL2-152 | Wortmann FX 73-CL2-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.6% at 43.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx73170-il,fx6617a2-il,fx73cl2152-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73170-il | 50,000 | 9 | 17.8 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 50,000 | 5 | 15.1 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170-il | 100,000 | 9 | 24.9 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 100,000 | 5 | 24.5 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170-il | 200,000 | 9 | 43.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 200,000 | 5 | 45.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170-il | 500,000 | 9 | 110.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 500,000 | 5 | 112.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170-il | 1,000,000 | 9 | 151.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 1,000,000 | 5 | 147.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 50,000 | 9 | 4.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 50,000 | 5 | 8.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 100,000 | 9 | 5.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 100,000 | 5 | 29.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 200,000 | 9 | 65 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 200,000 | 5 | 67.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 500,000 | 9 | 104.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 500,000 | 5 | 102 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 1,000,000 | 9 | 131.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 1,000,000 | 5 | 125.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 9 | 16.3 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 5 | 32.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 9 | 41.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 5 | 52.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 9 | 66.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 5 | 74.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 9 | 104.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 5 | 107.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 9 | 136.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 5 | 135.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||