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 | ||
(e656-il) EPPLER 656 AIRFOIL | Eppler E656 sailplane airfoil Max thickness 16.2% at 37% chord Max camber 4.8% at 42.2% chord | Remove Airfoil details Airfoil plotter |
(e639-il) EPPLER 639 AIRFOIL | Eppler E639 airfoil Max thickness 12.6% at 29.2% chord Max camber 4.8% at 29.2% chord | Remove Airfoil details Airfoil plotter |
(e63-il) E63 (4.25%) | Eppler E63 low Reynolds number airfoil Max thickness 4.3% at 22.8% chord Max camber 5.3% at 50.5% chord | Remove Airfoil details Airfoil plotter |
(e818-il) EPPLER 818 HYDROFOIL AIRFOIL | Eppler E818 hydrofoil Max thickness 9.4% at 33.1% chord Max camber 2.8% at 67% chord | Remove Airfoil details Airfoil plotter |
(e837-il) EPPLER E837 HYDROFOIL AIRFOIL | Eppler E837 hydrofoil Max thickness 16.1% at 36.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e656-il,e639-il,e63-il,e818-il,e837-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e656-il | 50,000 | 9 | 5.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 50,000 | 5 | 14.6 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 100,000 | 9 | 34.7 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 100,000 | 5 | 29.8 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 200,000 | 9 | 69.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 200,000 | 5 | 70.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 500,000 | 9 | 125.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 500,000 | 5 | 118.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 1,000,000 | 9 | 161.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 1,000,000 | 5 | 147.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e639-il | 50,000 | 9 | 13.3 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 50,000 | 5 | 25.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e639-il | 100,000 | 9 | 32.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 100,000 | 5 | 46 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e639-il | 200,000 | 9 | 62.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 200,000 | 5 | 69.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e639-il | 500,000 | 9 | 100.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 500,000 | 5 | 102.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e639-il | 1,000,000 | 9 | 131.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 1,000,000 | 5 | 129.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 50,000 | 9 | 52 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 50,000 | 5 | 51.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 100,000 | 9 | 77.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 100,000 | 5 | 77.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 200,000 | 9 | 112.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 200,000 | 5 | 110 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 500,000 | 9 | 176.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 500,000 | 5 | 160 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 9 | 235.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 5 | 157.7 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e818-il | 50,000 | 9 | 23.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 50,000 | 5 | 26.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e818-il | 100,000 | 9 | 66.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 100,000 | 5 | 40.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e818-il | 200,000 | 9 | 56.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 200,000 | 5 | 67.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e818-il | 500,000 | 9 | 104.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 500,000 | 5 | 96.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e818-il | 1,000,000 | 9 | 126.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e818-il | 1,000,000 | 5 | 110.2 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e837-il | 50,000 | 9 | 26.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e837-il | 50,000 | 5 | 25.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e837-il | 100,000 | 9 | 43.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e837-il | 100,000 | 5 | 37.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e837-il | 200,000 | 9 | 53 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e837-il | 200,000 | 5 | 50.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e837-il | 500,000 | 9 | 70.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e837-il | 500,000 | 5 | 61.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e837-il | 1,000,000 | 9 | 80.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e837-il | 1,000,000 | 5 | 65.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||