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 | ||
(e635-il) EPPLER 635 AIRFOIL | Eppler E635 airfoil Max thickness 11.6% at 26.2% chord Max camber 2.9% at 22.2% chord | Remove Airfoil details Airfoil plotter |
(avistar-il) AVISTAR | Hobbico R/C Avistar trainer airfoil Max thickness 14.5% at 34.2% chord Max camber 2.3% at 37.9% chord | Remove Airfoil details Airfoil plotter |
(goe404-il) GOE 404 AIRFOIL | Gottingen 404 airfoil Max thickness 13.2% at 29.6% chord Max camber 5% at 29.6% 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 |
(goe122-il) GOE 122 (MVA H.2) AIRFOIL | Gottingen 122 (MVA H.2) airfoil Max thickness 7.3% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e635-il,avistar-il,goe404-il,e1098-il,goe122-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e635-il | 50,000 | 9 | 14.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 50,000 | 5 | 24 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 100,000 | 9 | 36.3 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 100,000 | 5 | 43.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 200,000 | 9 | 60.6 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 200,000 | 5 | 64 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 500,000 | 9 | 92.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 500,000 | 5 | 88 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 1,000,000 | 9 | 113.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 1,000,000 | 5 | 100 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 50,000 | 9 | 30.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 50,000 | 5 | 31.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 100,000 | 9 | 49.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 100,000 | 5 | 46.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 200,000 | 9 | 63.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 200,000 | 5 | 59.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 500,000 | 9 | 81.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 500,000 | 5 | 72 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 1,000,000 | 9 | 93.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 1,000,000 | 5 | 71.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 50,000 | 9 | 15.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 50,000 | 5 | 31.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 100,000 | 9 | 45.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 100,000 | 5 | 50.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 200,000 | 9 | 68.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 200,000 | 5 | 69.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 500,000 | 9 | 98.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 500,000 | 5 | 94.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 1,000,000 | 9 | 121.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 1,000,000 | 5 | 110.7 at α=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 | |
| goe122-il | 50,000 | 9 | 37.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 50,000 | 5 | 39.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 100,000 | 9 | 55.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 100,000 | 5 | 56.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 200,000 | 9 | 73.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 200,000 | 5 | 72.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 500,000 | 9 | 95.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 500,000 | 5 | 89.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 1,000,000 | 9 | 110.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 1,000,000 | 5 | 97.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||