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 |
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Polars for (fx73cl1152-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 | |
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