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 | ||
(goe362-il) GOE 362 AIRFOIL | Gottingen 362 airfoil Max thickness 6.6% at 20% chord Max camber 5.3% at 40% chord | Remove Airfoil details Airfoil plotter |
(e68-il) EPPLER 68 AIRFOIL | Eppler E68 low Reynolds number airfoil Max thickness 13.1% at 32% chord Max camber 3.3% at 50.9% chord | Remove Airfoil details Airfoil plotter |
(e423-il) E423 | Eppler E423 high lift airfoil Max thickness 12.5% at 23.7% chord Max camber 9.5% at 41.4% chord | Remove Airfoil details Airfoil plotter |
(e205-il) E205 (10.48%) | Eppler E205 low Reynolds number airfoil Max thickness 10.5% at 29.7% chord Max camber 2.5% at 38.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe362-il,e68-il,e423-il,e205-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe362-il | 50,000 | 9 | 37.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 50,000 | 5 | 43.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 100,000 | 9 | 58.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 100,000 | 5 | 63.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 200,000 | 9 | 79.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 200,000 | 5 | 81.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 500,000 | 9 | 109.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 500,000 | 5 | 108.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 1,000,000 | 9 | 131.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 1,000,000 | 5 | 127.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 50,000 | 9 | 33.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 50,000 | 5 | 32.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 100,000 | 9 | 56.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 100,000 | 5 | 56.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 200,000 | 9 | 82.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 200,000 | 5 | 78.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 500,000 | 9 | 114.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 500,000 | 5 | 102.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 1,000,000 | 9 | 136.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 1,000,000 | 5 | 114.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 50,000 | 9 | 6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 50,000 | 5 | 13.9 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 100,000 | 9 | 12.5 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 100,000 | 5 | 51.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 200,000 | 9 | 73.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 200,000 | 5 | 84.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 500,000 | 9 | 123.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 500,000 | 5 | 120.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 1,000,000 | 9 | 156.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 1,000,000 | 5 | 145.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 50,000 | 9 | 32.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 50,000 | 5 | 34.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 100,000 | 9 | 53.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 100,000 | 5 | 54.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 200,000 | 9 | 75.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 200,000 | 5 | 74 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 500,000 | 9 | 105.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 500,000 | 5 | 98.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 1,000,000 | 9 | 128.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 1,000,000 | 5 | 116.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||