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 | ||
(e344-il) EPPLER 344 AIRFOIL | Eppler E344 flying wing airfoil Max thickness 14.7% at 29.9% chord Max camber 4.3% at 25% chord | Remove Airfoil details Airfoil plotter |
(ls413-il) NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL | NASA/Langley LS(1)-0413 (GA(W)-2) general aviation airfoil Max thickness 12.9% at 37.5% chord Max camber 2.4% at 65% chord | Remove Airfoil details Airfoil plotter |
(e337-il) EPPLER 337 AIRFOIL | Eppler E337 flying wing airfoil Max thickness 13.1% at 32% chord Max camber 3.2% at 22.4% chord | Remove Airfoil details Airfoil plotter |
(e403-il) EPPLER 403 AIRFOIL | Eppler E403 general purpose airfoil Max thickness 15% at 37.9% chord Max camber 3.2% at 75.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e344-il,ls413-il,e337-il,e403-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e344-il | 50,000 | 9 | 14.3 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 50,000 | 5 | 24.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 100,000 | 9 | 31.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 100,000 | 5 | 44 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 200,000 | 9 | 58 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 200,000 | 5 | 65.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 500,000 | 9 | 94.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 500,000 | 5 | 91.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 1,000,000 | 9 | 118.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 1,000,000 | 5 | 116.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 50,000 | 9 | 35.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 50,000 | 5 | 33.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 100,000 | 9 | 53 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 100,000 | 5 | 48.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 200,000 | 9 | 69.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 200,000 | 5 | 65.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 500,000 | 9 | 96.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 500,000 | 5 | 82.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413-il | 1,000,000 | 9 | 112.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413-il | 1,000,000 | 5 | 86.4 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 50,000 | 9 | 16 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 50,000 | 5 | 25.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 100,000 | 9 | 34.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 100,000 | 5 | 45.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 200,000 | 9 | 62.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 200,000 | 5 | 65.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 500,000 | 9 | 92.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 500,000 | 5 | 84.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 1,000,000 | 9 | 107.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 1,000,000 | 5 | 103.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e403-il | 50,000 | 9 | 33.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 50,000 | 5 | 29.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e403-il | 100,000 | 9 | 47.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 100,000 | 5 | 45.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e403-il | 200,000 | 9 | 66.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 200,000 | 5 | 66.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e403-il | 500,000 | 9 | 106.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 500,000 | 5 | 98.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e403-il | 1,000,000 | 9 | 138.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 1,000,000 | 5 | 115.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||