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 | ||
(goe100-il) GOE 100 (SOPWITH) AIRFOIL | Gottingen 100 (Sopwith) airfoil Max thickness 6.6% at 20% chord Max camber 3.6% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(e638-il) EPPLER 638 AIRFOIL | Eppler E638 airfoil Max thickness 12.4% at 28.5% chord Max camber 4.4% at 24.5% chord | Remove Airfoil details Airfoil plotter |
(rcsc2-il) NASA/LANGLEY RC-SC2 AIRFOIL | NASA/Langley RC-SC2 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 0.5% at 62.5% chord | Remove Airfoil details Airfoil plotter |
(e325-il) EPPLER 325 AIRFOIL | Eppler E325 flying wing airfoil Max thickness 12.6% at 34.3% chord Max camber 1.8% at 16.3% chord | Remove Airfoil details Airfoil plotter |
(e838-il) EPPLER E838 HYDROFOIL AIRFOIL | Eppler E838 hydrofoil Max thickness 18.4% at 37.2% chord Max camber 0% at 46.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe100-il,e638-il,rcsc2-il,e325-il,e838-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe100-il | 50,000 | 9 | 37.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 50,000 | 5 | 38 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 100,000 | 9 | 54.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 100,000 | 5 | 50.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 200,000 | 9 | 71.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 200,000 | 5 | 61.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 500,000 | 9 | 88.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 500,000 | 5 | 73.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 1,000,000 | 9 | 88.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 1,000,000 | 5 | 83.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 50,000 | 9 | 14.4 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 50,000 | 5 | 25.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 100,000 | 9 | 32.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 100,000 | 5 | 45.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 200,000 | 9 | 62.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 200,000 | 5 | 68.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 500,000 | 9 | 99.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 500,000 | 5 | 100.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 1,000,000 | 9 | 129.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 1,000,000 | 5 | 126 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 50,000 | 9 | 24.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 50,000 | 5 | 25.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 100,000 | 9 | 37.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 100,000 | 5 | 33.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 200,000 | 9 | 49.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 200,000 | 5 | 41.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 500,000 | 9 | 54.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 500,000 | 5 | 56.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 1,000,000 | 9 | 66.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 1,000,000 | 5 | 69.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 50,000 | 9 | 17.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 50,000 | 5 | 26.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 100,000 | 9 | 39.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 100,000 | 5 | 42.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 200,000 | 9 | 58.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 200,000 | 5 | 51.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 500,000 | 9 | 69.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 500,000 | 5 | 69.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 1,000,000 | 9 | 88.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 1,000,000 | 5 | 82.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 50,000 | 9 | 18.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 50,000 | 5 | 16.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 100,000 | 9 | 31.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 100,000 | 5 | 29.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 200,000 | 9 | 51.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 200,000 | 5 | 49.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 500,000 | 9 | 73.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 500,000 | 5 | 65 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 1,000,000 | 9 | 86.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 1,000,000 | 5 | 72.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||