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 | ||
(goe336-il) GOE 336 (MVA H.44) AIRFOIL | Gottingen 336 (MVA H.44) airfoil Max thickness 9% at 29.9% chord Max camber 5.4% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe289-il) GOE 289 (MVA 289) AIRFOIL | Gottingen 289 (MVA 289) airfoil Max thickness 16.8% at 30% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(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 |
(naca633418-il) NACA 63 | NACA 63 Max thickness 18% at 33.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe336-il,goe289-il,sg6050-il,naca633418-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe336-il | 50,000 | 9 | 30.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe336-il | 50,000 | 5 | 34.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe336-il | 100,000 | 9 | 56.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe336-il | 100,000 | 5 | 57.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe336-il | 200,000 | 9 | 79.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe336-il | 200,000 | 5 | 77.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe336-il | 500,000 | 9 | 107.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe336-il | 500,000 | 5 | 97.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe336-il | 1,000,000 | 9 | 125.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe336-il | 1,000,000 | 5 | 94.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe289-il | 50,000 | 9 | 4.3 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 50,000 | 5 | 20.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe289-il | 100,000 | 9 | 38.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 100,000 | 5 | 46.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe289-il | 200,000 | 9 | 65.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 200,000 | 5 | 64.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe289-il | 500,000 | 9 | 92.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 500,000 | 5 | 87.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe289-il | 1,000,000 | 9 | 115.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 1,000,000 | 5 | 109.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| naca633418-il | 50,000 | 9 | 20.3 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633418-il | 50,000 | 5 | 16.6 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633418-il | 100,000 | 9 | 45.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633418-il | 100,000 | 5 | 44.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633418-il | 200,000 | 9 | 69.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633418-il | 200,000 | 5 | 67.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633418-il | 500,000 | 9 | 99.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633418-il | 500,000 | 5 | 91.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633418-il | 1,000,000 | 9 | 120.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633418-il | 1,000,000 | 5 | 106.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||