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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(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 |
(ui1720-il) UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL | University of Illinois UI-1720 high lift airfoil Max thickness 13.8% at 19% chord Max camber 4.6% at 21.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ua79sff-il,ui1720-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| ui1720-il | 50,000 | 9 | 10.1 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ui1720-il | 50,000 | 5 | 17.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ui1720-il | 100,000 | 9 | 17.5 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ui1720-il | 100,000 | 5 | 29.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ui1720-il | 200,000 | 9 | 30.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ui1720-il | 200,000 | 5 | 44.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ui1720-il | 500,000 | 9 | 60.1 at α=15.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ui1720-il | 500,000 | 5 | 78 at α=15° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ui1720-il | 1,000,000 | 9 | 110.6 at α=16.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ui1720-il | 1,000,000 | 5 | 117.9 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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