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 | ||
(sg6050-il) SG6050 | Selig / Giguere SG6050 wind turbine airfoil Max thickness 16% at 31.5% chord Max camber 3.1% at 48.9% chord | Remove Airfoil details Airfoil plotter |
(goe188-il) GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL | Gottingen 188 (Schatte-Lanz 3U10) airfoil Max thickness 8.9% at 30% chord Max camber 4.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe406-il) GOE 406 AIRFOIL | Gottingen 406 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(ah93157-il) AH 93-157 | Althaus AH 93-157 airfoil Max thickness 15.7% at 39.6% chord Max camber 3.5% at 41.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (sg6050-il,goe188-il,goe406-il,ah93157-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sg6050-il | 50,000 | 9 | 8.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 50,000 | 5 | 25.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6050-il | 100,000 | 9 | 50 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 100,000 | 5 | 52.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6050-il | 200,000 | 9 | 74.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 200,000 | 5 | 73.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6050-il | 500,000 | 9 | 105.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 500,000 | 5 | 97.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6050-il | 1,000,000 | 9 | 126.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 1,000,000 | 5 | 113 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 50,000 | 9 | 31.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 50,000 | 5 | 39.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 100,000 | 9 | 51.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 100,000 | 5 | 57.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 200,000 | 9 | 71.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 200,000 | 5 | 74.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 500,000 | 9 | 98.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 500,000 | 5 | 99 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 1,000,000 | 9 | 119.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 1,000,000 | 5 | 116.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 50,000 | 9 | 17.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 50,000 | 5 | 34.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 100,000 | 9 | 54.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 100,000 | 5 | 53.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 200,000 | 9 | 75.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 200,000 | 5 | 68.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 500,000 | 9 | 94.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 500,000 | 5 | 89.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe406-il | 1,000,000 | 9 | 114.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe406-il | 1,000,000 | 5 | 112 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 50,000 | 9 | 4.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 50,000 | 5 | 14.4 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 100,000 | 9 | 40 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 100,000 | 5 | 37.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 200,000 | 9 | 74.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 200,000 | 5 | 66.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 500,000 | 9 | 100.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 500,000 | 5 | 92 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 1,000,000 | 9 | 120.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 1,000,000 | 5 | 112.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||