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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(fx73cl1152-il) FX 73-CL1-152 | Wortmann FX 73-CL1-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.1% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(fx79w470a-il) FX 79-W-470A | Wortmann FX 79-W-470A airfoil for use on wind turbines (W) Max thickness 46.4% at 37.1% chord Max camber 3.8% at 22.2% 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 |
(fx78k140-il) FX 78-K-140/20 | Wortmann FX 78-K-140/20 airfoil for use with flaps (K) Max thickness 14.1% at 43.5% chord Max camber 4.4% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(fx79w660a-il) FX 79-W-660A | Wortman FX 79-W-660A airfoil for use on wind turbines (W) Max thickness 66.4% at 46.7% chord Max camber 2.3% at 17% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx73cl1152-il,fx79w470a-il,fx84w218-il,fx78k140-il,fx79w660a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73cl1152-il | 50,000 | 9 | 4.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 50,000 | 5 | 20.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 100,000 | 9 | 24.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 100,000 | 5 | 42.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 200,000 | 9 | 53.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 200,000 | 5 | 68.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 500,000 | 9 | 100.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 500,000 | 5 | 106.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 1,000,000 | 9 | 137.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 1,000,000 | 5 | 136.8 at α=8.25° | 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 | |
| fx78k140-il | 50,000 | 9 | 16.3 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 50,000 | 5 | 15 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140-il | 100,000 | 9 | 26.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 100,000 | 5 | 27.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140-il | 200,000 | 9 | 54.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 200,000 | 5 | 53.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140-il | 500,000 | 9 | 125.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 500,000 | 5 | 122.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140-il | 1,000,000 | 9 | 162.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 1,000,000 | 5 | 153.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 50,000 | 9 | 0.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 50,000 | 5 | 3 at α=-10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 100,000 | 9 | 5.2 at α=-10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 100,000 | 5 | 5.5 at α=-5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 200,000 | 9 | 8.7 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 200,000 | 5 | 6 at α=-2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 500,000 | 9 | 5 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 500,000 | 5 | 4.7 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 1,000,000 | 9 | 6.5 at α=16.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 1,000,000 | 5 | 5.4 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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