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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(us1000root-il) US1000ROOT | Great Planes R/C Ultra-Sport 1000 airfoil Max thickness 18.6% at 27.1% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ultimate-il) ULTIMATE | Carl Goldberg R/C Ultimate Bipe airfoil Max thickness 12.8% at 34.2% chord Max camber 0% at 0% 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 (us1000root-il,ultimate-il,ui1720-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| us1000root-il | 50,000 | 9 | 19 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 50,000 | 5 | 24.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 100,000 | 9 | 38.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 100,000 | 5 | 38.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 200,000 | 9 | 49.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 200,000 | 5 | 44.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 500,000 | 9 | 49.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 500,000 | 5 | 43.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 1,000,000 | 9 | 52.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 1,000,000 | 5 | 45.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 50,000 | 9 | 28.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 50,000 | 5 | 27.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 100,000 | 9 | 39 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 100,000 | 5 | 36.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 200,000 | 9 | 47.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 200,000 | 5 | 42 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 500,000 | 9 | 55.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 500,000 | 5 | 53.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ultimate-il | 1,000,000 | 9 | 63.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ultimate-il | 1,000,000 | 5 | 67 at α=8° | 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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