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 | ||
(ua79sf18-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL | University of Alberta/Marsden UA 79-SF-187 FLAPPED sailplane airfoil Max thickness 18.8% at 42.8% chord Max camber 3.7% at 63.4% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ua79sf18-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ua79sf18-il | 50,000 | 9 | 15 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 50,000 | 5 | 15.2 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 100,000 | 9 | 24.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 100,000 | 5 | 23.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 200,000 | 9 | 37.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 200,000 | 5 | 35 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 500,000 | 9 | 65 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 500,000 | 5 | 75.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 1,000,000 | 9 | 133.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 1,000,000 | 5 | 114.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||