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 | ||
(sc20503-il) NASA SC(2)-0503 AIRFOIL | NASA SC(2)-0503 airfoil (NASA TP-2969) Max thickness 3% at 32% chord Max camber 0.8% at 82% chord | Remove Airfoil details Airfoil plotter |
(sc20612-il) NASA SC(2)-0612 AIRFOIL | NASA SC(2)-0612 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.9% at 81% chord | Remove Airfoil details Airfoil plotter |
(sg6043-il) SG6043 | Selig / Giguere SG6043 wind turbine airfoil (high L/D) Max thickness 10% at 32.1% chord Max camber 5.1% at 53.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (sc20503-il,sc20612-il,sg6043-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20503-il | 50,000 | 9 | 19.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 50,000 | 5 | 19.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20503-il | 100,000 | 9 | 26.5 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 100,000 | 5 | 24 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20503-il | 200,000 | 9 | 52.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 200,000 | 5 | 32.1 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20503-il | 500,000 | 9 | 50.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 500,000 | 5 | 35.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20503-il | 1,000,000 | 9 | 71.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 1,000,000 | 5 | 42.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 50,000 | 9 | 24.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 50,000 | 5 | 23.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 100,000 | 9 | 29.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 100,000 | 5 | 31.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 200,000 | 9 | 40.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 200,000 | 5 | 44.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 500,000 | 9 | 63.6 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 500,000 | 5 | 65 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 1,000,000 | 9 | 77.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 1,000,000 | 5 | 79.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6043-il | 50,000 | 9 | 39.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6043-il | 50,000 | 5 | 37.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6043-il | 100,000 | 9 | 66.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6043-il | 100,000 | 5 | 65.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6043-il | 200,000 | 9 | 98 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6043-il | 200,000 | 5 | 94.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6043-il | 500,000 | 9 | 143 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6043-il | 500,000 | 5 | 129.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6043-il | 1,000,000 | 9 | 175.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6043-il | 1,000,000 | 5 | 145.2 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||