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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(uag8814320-il) UAG 88-143/20 | UAG 88-143/20 airfoil Max thickness 14.3% at 43.5% chord Max camber 6.2% at 46.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (uag8814320-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| uag8814320-il | 50,000 | 9 | 5.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 50,000 | 5 | 15.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 100,000 | 9 | 32 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 100,000 | 5 | 30.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 200,000 | 9 | 55.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 200,000 | 5 | 53.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 500,000 | 9 | 127 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 500,000 | 5 | 123.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 1,000,000 | 9 | 185.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 1,000,000 | 5 | 169.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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