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 | ||
(e553-il) EPPLER 553 AIRFOIL | Eppler E553 general aviation airfoil Max thickness 18.1% at 31.8% chord Max camber 2.9% at 56.6% chord | Remove Airfoil details Airfoil plotter |
(e432-il) EPPLER 432 AIRFOIL | Eppler E432 sailplane airfoil Max thickness 16% at 37.4% chord Max camber 4.5% at 37.4% chord | Remove Airfoil details Airfoil plotter |
(e851-il) EPPLER E851 AIRFOIL | Eppler E851 propeller airfoil Max thickness 9% at 37% chord Max camber 2.3% at 66.3% chord | Remove Airfoil details Airfoil plotter |
(e550-il) EPPLER 550 AIRFOIL | Eppler E550 general aviation airfoil Max thickness 18.2% at 34% chord Max camber 2.2% at 29.4% chord | Remove Airfoil details Airfoil plotter |
(e479-il) EPPLER 479 AIRFOIL | Eppler E479 aerobatic aircraft airfoil Max thickness 16.6% at 25.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(e1098-il) EPPLER 1098 AIRFOIL | Eppler E1098 general aviation airfoil Max thickness 18.9% at 36.6% chord Max camber 3.7% at 54.5% chord | Remove Airfoil details Airfoil plotter |
(e420-il) EPPLER 420 AIRFOIL | Eppler E420 high lift airfoil Max thickness 14.3% at 22.8% chord Max camber 10.6% at 40.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e553-il,e432-il,e851-il,e550-il,e479-il,e1098-il,e420-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e553-il | 50,000 | 9 | 4.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 50,000 | 5 | 17.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 100,000 | 9 | 45.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 100,000 | 5 | 49.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 200,000 | 9 | 71.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 200,000 | 5 | 69.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 500,000 | 9 | 99.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 500,000 | 5 | 93.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 1,000,000 | 9 | 121.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 1,000,000 | 5 | 111.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e432-il | 50,000 | 9 | 5.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e432-il | 50,000 | 5 | 14.6 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e432-il | 100,000 | 9 | 36.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e432-il | 100,000 | 5 | 45.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e432-il | 200,000 | 9 | 75.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e432-il | 200,000 | 5 | 75.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e432-il | 231,000 | 9 | 81.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e432-il | 500,000 | 9 | 112.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e432-il | 500,000 | 5 | 108.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e432-il | 1,000,000 | 9 | 141.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e432-il | 1,000,000 | 5 | 131.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 50,000 | 9 | 27.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 50,000 | 5 | 31 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 100,000 | 9 | 49 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 100,000 | 5 | 50.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 200,000 | 9 | 77.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 200,000 | 5 | 73.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 500,000 | 9 | 110.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 500,000 | 5 | 90.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 1,000,000 | 9 | 122.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 1,000,000 | 5 | 95.7 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e550-il | 50,000 | 9 | 12.6 at α=-2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 50,000 | 5 | 11.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e550-il | 100,000 | 9 | 33.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 100,000 | 5 | 40.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e550-il | 200,000 | 9 | 66 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 200,000 | 5 | 67 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e550-il | 500,000 | 9 | 99.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 500,000 | 5 | 95.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e550-il | 1,000,000 | 9 | 124.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 1,000,000 | 5 | 114.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 50,000 | 9 | 15.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 50,000 | 5 | 23.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 100,000 | 9 | 33.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 100,000 | 5 | 39 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 200,000 | 9 | 52.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 200,000 | 5 | 54.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 500,000 | 9 | 76.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 500,000 | 5 | 74.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 1,000,000 | 9 | 95.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 1,000,000 | 5 | 88.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 50,000 | 9 | 5.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 50,000 | 5 | 14.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 100,000 | 9 | 29.8 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 100,000 | 5 | 24.9 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 200,000 | 9 | 51.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 200,000 | 5 | 63.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 500,000 | 9 | 117.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 500,000 | 5 | 112.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 1,000,000 | 9 | 151.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 1,000,000 | 5 | 139.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 50,000 | 9 | 5.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 50,000 | 5 | 13.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 100,000 | 9 | 20 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 100,000 | 5 | 47.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 200,000 | 9 | 63.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 200,000 | 5 | 75.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 500,000 | 9 | 107.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 500,000 | 5 | 106.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 1,000,000 | 9 | 137.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 1,000,000 | 5 | 134.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||