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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(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 |
(naca2424-il) NACA 2424 | NACA 2424 airfoil Max thickness 24% at 29.7% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe440-il) GOE 440 AIRFOIL | Gottingen 440 airfoil Max thickness 15.3% at 30% chord Max camber 9.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe602-il) GOE 602 AIRFOIL | Gottingen 602 airfoil Max thickness 10% at 30% chord Max camber 3.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx84w218-il,naca2424-il,goe440-il,goe602-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| naca2424-il | 50,000 | 9 | 1.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 50,000 | 5 | 15.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 100,000 | 9 | 36.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 100,000 | 5 | 33.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 200,000 | 9 | 49 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 200,000 | 5 | 40.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 500,000 | 9 | 55 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 500,000 | 5 | 49.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 1,000,000 | 9 | 65.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 1,000,000 | 5 | 58.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 50,000 | 9 | 9.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 50,000 | 5 | 31.9 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 100,000 | 9 | 53.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 100,000 | 5 | 52.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 200,000 | 9 | 71.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 200,000 | 5 | 67.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 500,000 | 9 | 92.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 500,000 | 5 | 86.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 1,000,000 | 9 | 109.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 1,000,000 | 5 | 100.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 50,000 | 9 | 37.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 50,000 | 5 | 39.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 100,000 | 9 | 57.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 100,000 | 5 | 57.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 200,000 | 9 | 77.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 200,000 | 5 | 74 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 500,000 | 9 | 102.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 500,000 | 5 | 93.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 1,000,000 | 9 | 119.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 1,000,000 | 5 | 104.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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