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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(s8065-il) S8065 (11% version of S8064) | Selig airfoil for Q-40 pylon racing (11%). Max thickness 11% at 37.8% chord Max camber 1.1% at 56.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s8065-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8065-il | 50,000 | 9 | 31.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 50,000 | 5 | 31.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8065-il | 100,000 | 9 | 49.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 100,000 | 5 | 46.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8065-il | 200,000 | 9 | 69 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 200,000 | 5 | 57.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8065-il | 500,000 | 9 | 80.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 500,000 | 5 | 64.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8065-il | 1,000,000 | 9 | 88.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 1,000,000 | 5 | 74.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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