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 | ||
(usa31-il) USA 31 AIRFOIL | USA-31 airfoil Max thickness 14.8% at 19.7% chord Max camber 9.3% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(ua79sff-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT | University of Alberta/Marsden UA 79-SF-187 sailplane airfoil FLAP Max thickness 8.7% at 73.1% chord Max camber 3.4% at 78.1% chord | Remove Airfoil details Airfoil plotter |
(ua79sfm-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT | University of Alberta/Marsden UA 79-SF-187 sailplane airfoil MAIN ELEMENT Max thickness 18.8% at 42.8% chord Max camber 3% at 66.9% chord | Remove Airfoil details Airfoil plotter |
(usa29-il) USA 29 AIRFOIL | USA-29 airfoil Max thickness 13.2% at 29.7% chord Max camber 5.5% at 39.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (usa31-il,ua79sff-il,ua79sfm-il,usa29-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa31-il | 50,000 | 9 | 4.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 50,000 | 5 | 14.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 100,000 | 9 | 34.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 100,000 | 5 | 40.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 200,000 | 9 | 62.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 200,000 | 5 | 54.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 500,000 | 9 | 76.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 500,000 | 5 | 69.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 1,000,000 | 9 | 88.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 1,000,000 | 5 | 79.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 50,000 | 9 | 3.4 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 50,000 | 5 | 3.5 at α=19.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 9 | 3.6 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 5 | 4.1 at α=18.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 9 | 3.8 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 5 | 5.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 9 | 6.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 5 | 25.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 9 | 60.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 5 | 62 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 50,000 | 9 | 12.2 at α=17.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 50,000 | 5 | 16.3 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 100,000 | 9 | 41.3 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 100,000 | 5 | 40.2 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 200,000 | 9 | 82.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 200,000 | 5 | 80 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 500,000 | 9 | 145.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 500,000 | 5 | 142.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 1,000,000 | 9 | 291 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 1,000,000 | 5 | 241.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 50,000 | 9 | 6.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 100,000 | 9 | 50.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 100,000 | 5 | 52.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 200,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 200,000 | 5 | 72.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 500,000 | 9 | 90 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 500,000 | 5 | 80.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 1,000,000 | 9 | 101.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 1,000,000 | 5 | 95.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||