Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(sd8000-il) SD8000-089-88 | Selig/Donovan SD8000 low Reynolds number airfoil Max thickness 8.9% at 29.4% chord Max camber 1.5% at 54% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (sd8000-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd8000-il | 50,000 | 9 | 33.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8000-il | 50,000 | 5 | 34.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd8000-il | 100,000 | 9 | 49.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8000-il | 100,000 | 5 | 46.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd8000-il | 200,000 | 9 | 64.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8000-il | 200,000 | 5 | 57.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd8000-il | 500,000 | 9 | 80.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8000-il | 500,000 | 5 | 74.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd8000-il | 1,000,000 | 9 | 92.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd8000-il | 1,000,000 | 5 | 87.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||