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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(n63210-il) NACA 63-210 AIRFOIL | NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord | Remove Airfoil details Airfoil plotter |
(naca1412-il) NACA 1412 | NACA 1412 airfoil Max thickness 12% at 29.9% chord Max camber 1% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca634421-il) NACA 63(4)-421 | NACA 63(4)-421 airfoil Max thickness 21% at 34.8% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(fx75193-il) WORTMANN FX 75-193 | Wortmann FX 75-193 airfoil Max thickness 19.3% at 40.2% chord Max camber 3.7% at 69.1% chord | Remove Airfoil details Airfoil plotter |
(goe517-il) GOE 517 AIRFOIL | Gottingen 517 airfoil Max thickness 7% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n63210-il,naca1412-il,naca634421-il,fx75193-il,goe517-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n63210-il | 50,000 | 9 | 33.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 50,000 | 5 | 32 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 100,000 | 9 | 46.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 100,000 | 5 | 42.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 200,000 | 9 | 59.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 200,000 | 5 | 48.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 500,000 | 9 | 67.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 500,000 | 5 | 55.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 1,000,000 | 9 | 69 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 1,000,000 | 5 | 66.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 50,000 | 9 | 29.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 50,000 | 5 | 31.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 100,000 | 9 | 44.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 100,000 | 5 | 43 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 200,000 | 9 | 57.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 200,000 | 5 | 53.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 500,000 | 9 | 73.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 500,000 | 5 | 66 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 1,000,000 | 9 | 83.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 1,000,000 | 5 | 78.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 50,000 | 9 | 3.8 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 50,000 | 5 | 9.4 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 100,000 | 9 | 24.4 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 100,000 | 5 | 35 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 200,000 | 9 | 61.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 200,000 | 5 | 63 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 500,000 | 9 | 95.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 500,000 | 5 | 90.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634421-il | 1,000,000 | 9 | 119.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634421-il | 1,000,000 | 5 | 109.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 50,000 | 9 | 4.2 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 50,000 | 5 | 11.7 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 9 | 23.4 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 5 | 22.9 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 9 | 43.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 5 | 44.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 9 | 91.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 5 | 93.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 9 | 122.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 5 | 120.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 50,000 | 9 | 37.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 50,000 | 5 | 40.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 100,000 | 9 | 55.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 100,000 | 5 | 60.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 200,000 | 9 | 75 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 200,000 | 5 | 79.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 500,000 | 9 | 103 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 500,000 | 5 | 102 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 1,000,000 | 9 | 121.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 1,000,000 | 5 | 117.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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