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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(sd7084-il) SD7084 (9.6%) | Selig/Donovan SD7084 low Reynolds number airfoil Max thickness 9.6% at 29.5% chord Max camber 2.3% at 38.9% chord | Remove Airfoil details Airfoil plotter |
(fx63143-il) FX 63-143 AIRFOIL | Wortmann FX 63-143 airfoil Max thickness 14.3% at 33.9% chord Max camber 3.1% at 30.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd7084-il,fx63143-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd7084-il | 50,000 | 9 | 31.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 50,000 | 5 | 35.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 100,000 | 9 | 49.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 100,000 | 5 | 49.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 200,000 | 9 | 65.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 200,000 | 5 | 63.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 500,000 | 9 | 87.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 500,000 | 5 | 83.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 1,000,000 | 9 | 104.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 1,000,000 | 5 | 98.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 50,000 | 9 | 10.7 at α=-1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 50,000 | 5 | 24 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 100,000 | 9 | 46.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 100,000 | 5 | 49.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 200,000 | 9 | 72.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 200,000 | 5 | 65.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 500,000 | 9 | 71 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 500,000 | 5 | 64.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 1,000,000 | 9 | 79.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 1,000,000 | 5 | 78.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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