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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(goe693-il) GOE 693 AIRFOIL | Gottingen 693 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(fx84w218-il) FX 84-W-218 | Wortmann FX 84-W-218 airfoil for use on wind turbines (W) Max thickness 22% at 33.9% chord Max camber 3.2% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(n63012a-il) NACA 63012A AIRFOIL | NACA 63-012A airfoil Max thickness 12% at 35% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe693-il,fx84w218-il,n63012a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe693-il | 50,000 | 9 | 32.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 50,000 | 5 | 35.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe693-il | 100,000 | 9 | 56 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 100,000 | 5 | 55.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe693-il | 200,000 | 9 | 78.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 200,000 | 5 | 72.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe693-il | 500,000 | 9 | 103.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 500,000 | 5 | 87.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe693-il | 1,000,000 | 9 | 115.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe693-il | 1,000,000 | 5 | 97.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w218-il | 50,000 | 9 | 2.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w218-il | 50,000 | 5 | 6.7 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w218-il | 100,000 | 9 | 7.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w218-il | 100,000 | 5 | 24.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w218-il | 200,000 | 9 | 57.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w218-il | 200,000 | 5 | 49.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w218-il | 500,000 | 9 | 79.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w218-il | 500,000 | 5 | 72.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w218-il | 1,000,000 | 9 | 101.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w218-il | 1,000,000 | 5 | 90.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63012a-il | 50,000 | 9 | 28.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 50,000 | 5 | 28.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63012a-il | 100,000 | 9 | 41.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 100,000 | 5 | 38.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63012a-il | 200,000 | 9 | 52 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 200,000 | 5 | 41.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63012a-il | 500,000 | 9 | 58.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 500,000 | 5 | 54.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63012a-il | 1,000,000 | 9 | 64.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 1,000,000 | 5 | 66.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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