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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(n66021-il) NACA 66-021 AIRFOIL | NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(sc20402-il) NASA SC(2)-0402 AIRFOIL | NASA SC(2)-0402 airfoil (NASA TP-2969) Max thickness 2% at 34% chord Max camber 0.5% at 83% chord | Remove Airfoil details Airfoil plotter |
(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 |
(sg6040-il) SG6040 | Selig / Giguere SG6040 wind turbine airfoil Max thickness 16% at 35.3% chord Max camber 2.3% at 60.5% chord | Remove Airfoil details Airfoil plotter |
(oaf095-il) OAF095 AIRFOIL | ONERA/Aerospatiale OAF095 Fenestron airfoil Max thickness 9.5% at 23.2% chord Max camber 3.9% at 53.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n66021-il,sc20402-il,sc20503-il,sg6040-il,oaf095-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n66021-il | 50,000 | 9 | 18.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 50,000 | 5 | 11 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 100,000 | 9 | 23.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 100,000 | 5 | 15.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 200,000 | 9 | 25.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 200,000 | 5 | 26.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 500,000 | 9 | 57.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 500,000 | 5 | 54.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 1,000,000 | 9 | 78.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 1,000,000 | 5 | 64.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20402-il | 50,000 | 9 | 14.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20402-il | 50,000 | 5 | 14.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20402-il | 100,000 | 9 | 16.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20402-il | 100,000 | 5 | 16.9 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20402-il | 200,000 | 9 | 20.1 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20402-il | 200,000 | 5 | 40.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20402-il | 500,000 | 0 | 64.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20402-il | 1,000,000 | 9 | 32.7 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| 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 | |
| sg6040-il | 50,000 | 9 | 26.1 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 50,000 | 5 | 26.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 100,000 | 9 | 50.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 100,000 | 5 | 50.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 200,000 | 9 | 72.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 200,000 | 5 | 68.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 500,000 | 9 | 96.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 500,000 | 5 | 88.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 1,000,000 | 9 | 114.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 1,000,000 | 5 | 102.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 50,000 | 9 | 43.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 50,000 | 5 | 43.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 9 | 65.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 5 | 63.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 9 | 88.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 5 | 82.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 9 | 116.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 5 | 93.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 9 | 131.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 5 | 98.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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