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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(sd8040-il) SD8040 (10%) | Selig/Donovan SD8040 low Reynolds number airfoil Max thickness 10% at 29.7% chord Max camber 2.1% at 44% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd8040-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd8040-il | 50,000 | 9 | 32.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8040-il | 50,000 | 5 | 36.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd8040-il | 100,000 | 9 | 51.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8040-il | 100,000 | 5 | 51.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd8040-il | 200,000 | 9 | 69.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8040-il | 200,000 | 5 | 65.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd8040-il | 500,000 | 9 | 91.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8040-il | 500,000 | 5 | 84.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd8040-il | 1,000,000 | 9 | 107.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8040-il | 1,000,000 | 5 | 99 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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