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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(fx082512-il) WORTMANN FX 082-512 AIRFOIL | Wortmann FX 082-512 airfoil Max thickness 11.8% at 25% chord Max camber 4.2% at 62.9% chord | Remove Airfoil details Airfoil plotter |
(s4083-il) S4083 (8%) | Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx082512-il,s4083-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx082512-il | 50,000 | 9 | 31.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 50,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 100,000 | 9 | 46.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 100,000 | 5 | 47.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 200,000 | 9 | 63.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 200,000 | 5 | 60.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 500,000 | 9 | 83.7 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 500,000 | 5 | 75.3 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 1,000,000 | 9 | 99.1 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 1,000,000 | 5 | 82.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 50,000 | 9 | 31.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 50,000 | 5 | 38.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 9 | 51.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 5 | 56.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 9 | 73.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 5 | 74.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 9 | 102.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 5 | 98.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 9 | 124.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 5 | 115.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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