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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(fx73cl3152-il) FX 73-CL3-152 | Wortmann FX 73-CL3-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 8% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx73cl3152-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73cl3152-il | 50,000 | 9 | 5.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 50,000 | 5 | 28.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 100,000 | 9 | 38.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 100,000 | 5 | 50.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 200,000 | 9 | 64 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 200,000 | 5 | 71 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 500,000 | 9 | 99.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 500,000 | 5 | 100.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl3152-il | 1,000,000 | 9 | 129.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl3152-il | 1,000,000 | 5 | 128.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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