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 | ||
(e178-il) E178 (8.69%) | Eppler E178 low Reynolds number airfoil Max thickness 8.7% at 29.8% chord Max camber 2.8% at 38.8% chord | Remove Airfoil details Airfoil plotter |
(e182-il) E182 (8.47%) | Eppler E182 low Reynolds number airfoil Max thickness 8.5% at 32.4% chord Max camber 1.2% at 37.5% chord | Remove Airfoil details Airfoil plotter |
(e176-il) E176 (8.83%) | Eppler E176 low Reynolds number airfoil Max thickness 8.8% at 30.5% chord Max camber 2.9% at 44.2% chord | Remove Airfoil details Airfoil plotter |
(e1214-il) EPPLER 1214 AIRFOIL | Eppler E1214 general aviation airfoil Max thickness 19.8% at 26.2% chord Max camber 2.1% at 30.4% chord | Remove Airfoil details Airfoil plotter |
(e1213-il) EPPLER 1213 AIRFOIL | Eppler E1213 general aviation airfoil Max thickness 17.4% at 22.1% chord Max camber 2.1% at 35.1% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e178-il,e182-il,e176-il,e1214-il,e1213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e178-il | 50,000 | 9 | 36.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 50,000 | 5 | 37.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 100,000 | 9 | 56.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 100,000 | 5 | 55.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 200,000 | 9 | 77.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 200,000 | 5 | 73.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 500,000 | 9 | 105 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 500,000 | 5 | 95.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 1,000,000 | 9 | 125.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 1,000,000 | 5 | 108.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e182-il | 50,000 | 9 | 32.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 50,000 | 5 | 34.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e182-il | 100,000 | 9 | 48.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 100,000 | 5 | 47 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e182-il | 200,000 | 9 | 64.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 200,000 | 5 | 58.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e182-il | 500,000 | 9 | 81.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 500,000 | 5 | 71.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e182-il | 1,000,000 | 9 | 92.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 1,000,000 | 5 | 78.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e176-il | 50,000 | 9 | 37.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e176-il | 50,000 | 5 | 38.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e176-il | 100,000 | 9 | 59.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e176-il | 100,000 | 5 | 58.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e176-il | 200,000 | 9 | 81.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e176-il | 200,000 | 5 | 78.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e176-il | 500,000 | 9 | 110.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e176-il | 500,000 | 5 | 103.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e176-il | 1,000,000 | 9 | 132.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e176-il | 1,000,000 | 5 | 119.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 50,000 | 9 | 3.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 50,000 | 5 | 18.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 9 | 25.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 5 | 36.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 9 | 48.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 5 | 54 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 9 | 78.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 5 | 80.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 9 | 105.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 5 | 103.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 50,000 | 9 | 11.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 50,000 | 5 | 22.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 100,000 | 9 | 30.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 100,000 | 5 | 39.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 200,000 | 9 | 51.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 200,000 | 5 | 55.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 500,000 | 9 | 79.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 500,000 | 5 | 80.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 1,000,000 | 9 | 102.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 1,000,000 | 5 | 101.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||