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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(fx74130wp1-il) FX 74-130 WP1 | Wortmann FX 74-130 WP1 airfoil Max thickness 13% at 46.7% chord Max camber 3.8% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx74130wp1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74130wp1-il | 50,000 | 9 | 24.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 50,000 | 5 | 23.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp1-il | 100,000 | 9 | 39.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 100,000 | 5 | 39.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp1-il | 200,000 | 9 | 72 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 200,000 | 5 | 71.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp1-il | 500,000 | 9 | 119.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 500,000 | 5 | 115.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp1-il | 1,000,000 | 9 | 152.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 1,000,000 | 5 | 145.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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