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 | ||
(goe06k-il) GOE 6K AIRFOIL | Gottingen 6K airfoil Max thickness 7.5% at 50% chord Max camber 3.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(s7075-il) S7075 (9%) | Selig S7075 low Reynolds number airfoil Max thickness 9% at 29% chord Max camber 2.8% at 46.8% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe06k-il,s7075-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe06k-il | 50,000 | 9 | 26.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 50,000 | 5 | 28.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe06k-il | 100,000 | 9 | 45.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 100,000 | 5 | 44.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe06k-il | 200,000 | 9 | 74.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 200,000 | 5 | 77 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe06k-il | 500,000 | 9 | 117.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 500,000 | 5 | 116.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe06k-il | 1,000,000 | 9 | 147.6 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 1,000,000 | 5 | 132.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 50,000 | 9 | 38.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 50,000 | 5 | 40.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 100,000 | 9 | 59.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 100,000 | 5 | 57.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 200,000 | 9 | 81.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 200,000 | 5 | 74 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 500,000 | 9 | 108 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 500,000 | 5 | 91.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 1,000,000 | 9 | 123 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 1,000,000 | 5 | 101.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||