Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(naca651412-il) NACA 65(1)-412 | NACA 65(1)-412 airfoil Max thickness 12% at 39.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(ah82150a-il) AH 82-150 A | Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(sg6041-il) SG6041 | Selig / Giguere SG6041 wind turbine airfoil (high L/D) Max thickness 10% at 34.9% chord Max camber 1.6% at 49.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca651412-il,ah82150a-il,sg6041-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca651412-il | 50,000 | 9 | 28.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 50,000 | 5 | 30.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 100,000 | 9 | 53 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 100,000 | 5 | 51.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 200,000 | 9 | 74.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 200,000 | 5 | 67.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 500,000 | 9 | 98.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 500,000 | 5 | 88.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 1,000,000 | 9 | 116.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 1,000,000 | 5 | 100.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 50,000 | 9 | 17.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 50,000 | 5 | 20.2 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 9 | 42.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 5 | 41.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 9 | 72.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 5 | 73.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 9 | 108.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 5 | 107.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 9 | 137.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 5 | 129.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 50,000 | 9 | 35.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 50,000 | 5 | 35.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 100,000 | 9 | 53.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 100,000 | 5 | 49.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 200,000 | 9 | 72.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 200,000 | 5 | 63.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 500,000 | 9 | 91.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 500,000 | 5 | 74.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 1,000,000 | 9 | 96.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 1,000,000 | 5 | 88 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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