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 | ||
(e392-il) E392 (10.15%) | Eppler E392 low Reynolds number airfoil Max thickness 10.1% at 31.6% chord Max camber 3.7% at 45.3% chord | Remove Airfoil details Airfoil plotter |
(e58-il) EPPLER 58 AIRFOIL | Eppler E58 low Reynolds number airfoil Max thickness 5.6% at 30% chord Max camber 6.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(fx63120-il) FX 63-120 AIRFOIL | Wortmann FX 63-120 airfoil Max thickness 12% at 30.8% chord Max camber 5.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(fx76mp120-il) FX 76-MP-120 | Wortmann FX 76-MP-120 airfoil Max thickness 12.1% at 33.9% chord Max camber 7.6% at 46.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e392-il,e58-il,fx63120-il,fx76mp120-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e392-il | 50,000 | 9 | 37.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 50,000 | 5 | 37.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e392-il | 100,000 | 9 | 61.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 100,000 | 5 | 61.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e392-il | 200,000 | 9 | 86.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 200,000 | 5 | 84.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e392-il | 500,000 | 9 | 120.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 500,000 | 5 | 113.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e392-il | 1,000,000 | 9 | 146.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e392-il | 1,000,000 | 5 | 134 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 50,000 | 9 | 46.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 50,000 | 5 | 44.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 100,000 | 9 | 70.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 100,000 | 5 | 68.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 200,000 | 9 | 108.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 200,000 | 5 | 106.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 500,000 | 9 | 175.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 500,000 | 5 | 166.6 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 1,000,000 | 9 | 235.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 1,000,000 | 5 | 160.8 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63120-il | 50,000 | 9 | 36.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63120-il | 50,000 | 5 | 40 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63120-il | 100,000 | 9 | 64.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63120-il | 100,000 | 5 | 67.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63120-il | 200,000 | 9 | 93.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63120-il | 200,000 | 5 | 90 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63120-il | 500,000 | 9 | 125.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63120-il | 500,000 | 5 | 114.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63120-il | 1,000,000 | 9 | 147.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63120-il | 1,000,000 | 5 | 129.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp120-il | 50,000 | 9 | 6.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 50,000 | 5 | 16.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp120-il | 100,000 | 9 | 42.9 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 100,000 | 5 | 41.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp120-il | 200,000 | 9 | 85.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 200,000 | 5 | 88.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp120-il | 500,000 | 9 | 147.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 500,000 | 5 | 141.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp120-il | 1,000,000 | 9 | 192.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp120-il | 1,000,000 | 5 | 174 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||