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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(ua2-180sm-il) UA(2)-180 smoothed | UA(2)-180 (smoothed) airfoil for ultralight category aircraft Max thickness 18.2% at 34.1% chord Max camber 6.5% at 39.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ua2-180sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ua2-180sm-il | 50,000 | 9 | 3.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 50,000 | 5 | 6.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 100,000 | 9 | 4.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 100,000 | 5 | 23.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 200,000 | 9 | 27.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 200,000 | 5 | 55.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 500,000 | 9 | 102.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 500,000 | 5 | 106.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 1,000,000 | 9 | 146.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 1,000,000 | 5 | 145.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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