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 | ||
(fx61163-il) FX 61-163 AIRFOIL | Wortmann FX 61-163 airfoil Max thickness 16.4% at 37.1% chord Max camber 2.6% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(fx60157-il) FX 60-157 AIRFOIL | Wortmann FX 60-157 airfoil Max thickness 15.7% at 40.2% chord Max camber 2.7% at 75% chord | Remove Airfoil details Airfoil plotter |
(fx72150a-il) WORTMANN FX 72-MS-150A AIRFOIL | Wortmann FX 72-MS-150A airfoil Max thickness 15% at 37.1% chord Max camber 8.3% at 46.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx61163-il,fx60157-il,fx72150a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61163-il | 50,000 | 9 | 6.1 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 50,000 | 5 | 19.4 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 100,000 | 9 | 47.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 100,000 | 5 | 50 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 200,000 | 9 | 70.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 200,000 | 5 | 72.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 500,000 | 9 | 103.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 500,000 | 5 | 98.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 1,000,000 | 5 | 115.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 1,000,000 | 0 | 127.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 50,000 | 9 | 28.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 50,000 | 5 | 28.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60157-il | 100,000 | 9 | 46.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 100,000 | 5 | 41.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60157-il | 200,000 | 9 | 56.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 200,000 | 5 | 57.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60157-il | 500,000 | 9 | 81.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 500,000 | 5 | 70 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60157-il | 1,000,000 | 9 | 95.8 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 1,000,000 | 5 | 72.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 50,000 | 9 | 6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 50,000 | 5 | 10.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 100,000 | 9 | 13.2 at α=15.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 100,000 | 5 | 40.5 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 200,000 | 9 | 58.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 200,000 | 5 | 78.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 500,000 | 9 | 123.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 500,000 | 5 | 121.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 1,000,000 | 9 | 160.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 1,000,000 | 5 | 154 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||