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 | ||
(s3016-il) S3016-095-87 | Selig S3016 low Reynolds number airfoil Max thickness 9.5% at 28.9% chord Max camber 1.8% at 43.1% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s3016-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s3016-il | 50,000 | 9 | 31.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 50,000 | 5 | 34.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3016-il | 100,000 | 9 | 49.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 100,000 | 5 | 48.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3016-il | 200,000 | 9 | 65.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 200,000 | 5 | 61 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3016-il | 500,000 | 9 | 85.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 500,000 | 5 | 78.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3016-il | 1,000,000 | 9 | 99.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3016-il | 1,000,000 | 5 | 93.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||