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 | ||
(e338-il) EPPLER 338 AIRFOIL | Eppler E338 flying wing airfoil Max thickness 13.3% at 31.1% chord Max camber 3.7% at 26.2% chord | Remove Airfoil details Airfoil plotter |
(e668-il) EPPLER 668 AIRFOIL | Eppler E668 sailplane airfoil Max thickness 13.9% at 37.3% chord Max camber 4% at 47.8% chord | Remove Airfoil details Airfoil plotter |
(e662-il) EPPLER E662 AIRFOIL | Eppler E662 sailplane airfoil Max thickness 15% at 42.8% chord Max camber 4.1% at 47.5% chord | Remove Airfoil details Airfoil plotter |
(e201-il) E201 (11.88%) | Eppler E201 low Reynolds number airfoil Max thickness 11.9% at 30.8% chord Max camber 2.6% at 49.4% chord | Remove Airfoil details Airfoil plotter |
(e598-il) EPPLER 598 AIRFOIL | Eppler E598 airfoil Max thickness 11.1% at 24.2% chord Max camber 4.5% at 34.4% chord | Remove Airfoil details Airfoil plotter |
(e335-il) EPPLER 335 AIRFOIL | Eppler E335 flying wing airfoil Max thickness 12.6% at 29% chord Max camber 2.3% at 19.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e338-il,e668-il,e662-il,e201-il,e598-il,e335-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e338-il | 50,000 | 9 | 15.8 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 50,000 | 5 | 26.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e338-il | 100,000 | 9 | 33.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 100,000 | 5 | 45.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e338-il | 200,000 | 9 | 63.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 200,000 | 5 | 67.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e338-il | 500,000 | 9 | 97.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 500,000 | 5 | 88.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e338-il | 1,000,000 | 9 | 114 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 1,000,000 | 5 | 108.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 50,000 | 9 | 31 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 50,000 | 5 | 27 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 100,000 | 9 | 51.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 100,000 | 5 | 47.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 200,000 | 9 | 81.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 200,000 | 5 | 77.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 500,000 | 9 | 123 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 500,000 | 5 | 113.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 1,000,000 | 9 | 155.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 1,000,000 | 5 | 135.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 50,000 | 9 | 27.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 50,000 | 5 | 23.4 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 100,000 | 9 | 46.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 100,000 | 5 | 40.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 200,000 | 9 | 71.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 200,000 | 5 | 66.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 500,000 | 9 | 114.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 500,000 | 5 | 111.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 1,000,000 | 9 | 152 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 1,000,000 | 5 | 138.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 50,000 | 9 | 34 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 50,000 | 5 | 33.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 100,000 | 9 | 56.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 100,000 | 5 | 57 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 200,000 | 9 | 80.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 200,000 | 5 | 78.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 500,000 | 9 | 112 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 500,000 | 5 | 104.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 1,000,000 | 9 | 135.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 1,000,000 | 5 | 122.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 50,000 | 9 | 9.9 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 50,000 | 5 | 23.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 100,000 | 9 | 43.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 100,000 | 5 | 50.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 200,000 | 9 | 72.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 200,000 | 5 | 75.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 500,000 | 9 | 109.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 500,000 | 5 | 106.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 1,000,000 | 9 | 137.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 1,000,000 | 5 | 128.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 50,000 | 9 | 15.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 50,000 | 5 | 25.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 100,000 | 9 | 38.3 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 100,000 | 5 | 44.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 200,000 | 9 | 60.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 200,000 | 5 | 58.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 500,000 | 9 | 81.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 500,000 | 5 | 72 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 1,000,000 | 9 | 90.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 1,000,000 | 5 | 88.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||